A dual-element nozzle for an engine

Abstract

The present application belongs to the field of engine dual nozzle design, and specifically relates to an engine dual nozzle, which is designed to introduce external low-temperature gas to cool the internal and external components such as the convergent section, the expansion section, the outer adjustment plate, the front side wall, the rear side wall, and the side wall cover along the way. The flow rate of the low-temperature gas can be controlled to ensure the cooling effect of the internal and external components, improve the performance, and avoid the internal components from being burned, and the external components from being deformed or warped, and no additional external airflow is required. In addition, when the engine is in a large working condition or needs to be rapidly cooled to improve the infrared stealth capability, the phase change cooling medium can be used to rapidly cool the front side wall, the rear side wall, and the side wall cover, and reduce the temperature of the front side wall, the rear side wall, and the side wall cover in a short time, thereby avoiding the dual nozzle components from being burned and improving the infrared stealth capability of the engine.

Description

Technical Field

[0001] The present application belongs to the field of engine dual nozzle design, and specifically relates to an engine dual nozzle. Background Art

[0002] The engine's dual nozzle is installed at the end of the engine, and uses the contraction and expansion movement of internal components such as the convergent section and the divergent section for vector adjustment. It is also designed with external components such as external adjustment plates and side wall covers to protect internal components from direct damage by external forces, to rectify the exterior, and to reduce rear body resistance.

[0003] The engine's dual nozzle is subjected to high-temperature airflow and bears extremely high temperature loads. Its components are easily ablated and have obvious infrared radiation characteristics. To this end, currently, the engine's external airflow is mostly used to cool the dual nozzle components, reduce the temperature of the dual nozzle components, avoid the dual nozzle components from being ablated, and suppress infrared radiation characteristics to enhance infrared stealth capabilities. However, the external airflow also needs to be used to cool and reduce the temperature of other necessary high-temperature components. The cooling capacity that can be provided for the dual nozzle is limited and cannot well meet the cooling needs of the dual nozzle.

[0004] This application is proposed in view of the above-mentioned technical defects.

[0005] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of 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 technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0006] The purpose of this application is to provide an engine dual nozzle to overcome or alleviate at least one of the technical deficiencies of the known ones.

[0007] The technical solution of this application is:

[0008] An engine dual nozzle, comprising:

[0009] The circular rotating square section has a front end connected to the rear end of the engine, and the outer wall of the rear end has a connecting edge;

[0010] The two convergent sections have front ends hinged to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section, and the connecting edges of the two opposite side walls at the rear end of the circular rotating square section are provided with cooling air ducting holes;

[0011] Two expansion sections, the front end of which is hinged to the rear end of the two convergent sections;

[0012] Two outer adjustment plates are located outside the two convergent sections and the expansion section, with their front ends hinged to the connecting edges of the two opposite side walls at the rear end of the circular-square section, and multiple cooling exhaust holes are distributed on the rear end side walls;

[0013] The front ends of the two front section side walls are connected to the connecting edges of the other two opposite side walls at the rear end of the circular rotating square section, and the two opposite side walls at the rear end of the circular rotating square section have a clearance hole; a cooling air bleed cavity is formed between the two front section side walls and the two convergent sections, the expansion section, and the outer adjustment plate, and a plurality of cooling communication holes are distributed on the cooling air bleed cavity; the cooling air bleed cavity is connected to each cooling air bleed hole, the cooling exhaust hole, and the cooling communication hole;

[0014] The front ends of the two rear side walls are connected to the rear ends of the two front side walls, and a rear exhaust gap is formed between the rear ends of the two front side walls, and a plurality of air film holes are provided on the wall surface;

[0015] The two side wall covers are located outside the two front side walls and the rear side walls, with the front ends correspondingly connected to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section, and connected to the two front side walls and the rear side walls along the edges, forming a cooling exhaust cavity between the two front side walls and the rear side walls; the cooling exhaust cavity is connected to each cooling connecting hole, the rear exhaust slit, and the air film hole;

[0016] One end of two phase-change cooling medium jet tubes passes through two clearance holes and extends into the cooling exhaust cavity. The side wall of the portion extending into the cooling exhaust cavity has multiple jet holes distributed along the axial direction.

[0017] According to at least one embodiment of the present application, in the aforementioned engine dual nozzle, the two expansion sections and the rear end of the outer adjustment plate are in a pointed cone shape;

[0018] The cooling exhaust holes are distributed along the two expansion sections and the rear edge of the outer adjustment plate;

[0019] The two front side walls, the rear side wall and the side wall cover are V-shaped as a whole;

[0020] The rear exhaust slit is in a V-shape that expands rearward.

[0021] According to at least one embodiment of the present application, in the above-mentioned engine dual nozzle, the flow area of ​​the two cooling air bleed holes is 1 to 2 times the flow area of ​​each cooling exhaust hole and cooling connecting hole;

[0022] The flow area of ​​each cooling connection hole is 1 to 2 times the flow area of ​​the two rear exhaust slits;

[0023] Two phase-change cooling medium jet pipes extend into one end of the cooling exhaust cavity and are blocked, and the flow area is 1.75 to 2 times the area of ​​the jet holes thereon.

[0024] According to at least one embodiment of the present application, in the aforementioned engine dual nozzle, the two outer adjustment plates converge inwardly.

[0025] According to at least one embodiment of the present application, in the above-mentioned engine dual nozzle, the number of jet holes on each of the two phase-change coolant jet tubes is an odd number greater than three, and they are oriented toward the two rear side walls or side wall covers, with the angle between them and the rear side walls or side wall covers not exceeding 90°, and the middle jet hole is perpendicular to the rear side walls or side wall covers.

[0026] According to at least one embodiment of the present application, the above-mentioned engine dual nozzle further includes:

[0027] Two partitions are provided in the two cooling exhaust cavities to divide the cooling exhaust cavities into a front cooling exhaust cavity and a rear cooling exhaust cavity corresponding to the front side wall and the rear side wall, wherein the front cooling exhaust cavity is connected to each cooling communication hole and the rear exhaust slit; and the rear cooling exhaust cavity is connected to each air film hole;

[0028] Two phase change cooling medium jet tubes are set through the partition, and the upper jet holes are partially located in the front cooling exhaust cavity and partially located in the rear cooling exhaust cavity, and the distribution density of the jet holes in the rear cooling exhaust cavity is greater than the distribution density of the jet holes in the front cooling exhaust cavity.

[0029] According to at least one embodiment of the present application, the above-mentioned engine dual nozzle further includes:

[0030] Two gaskets are sleeved on the outer peripheries of the two phase-change cooling medium jet tubes and welded to the outer sides of the connecting edges of the two opposite side walls;

[0031] The two connecting flanges are sleeved on the two phase change cooling medium jet tubes, and the stoppers between the two gaskets are centered and positioned, and a sealing gasket is arranged therebetween. The two gaskets are connected by bolts, and a spring washer is arranged between the bolt head and the connecting flange.

[0032] According to at least one embodiment of the present application, in the above-mentioned engine dual nozzle, the phase change cooling medium jet tubes and their corresponding components are divided into two groups corresponding to the two cooling exhaust cavities, with each group consisting of two.

[0033] This application has at least the following beneficial technical effects:

[0034] Provided is an engine dual nozzle, which is designed to introduce external low-temperature gas to cool internal and external components such as the convergent section, the divergent section, the outer adjustment plate, the front section side wall, the rear section side wall, and the side wall outer cover along the way. The cooling effect of the internal and external components and the body performance can be guaranteed by controlling the flow rate of the low-temperature gas, and the internal components can be avoided from being eroded, and the external components can be deformed and warped. There is no need to additionally occupy the external airflow. In addition, when the engine is in a large operating condition or needs to be rapidly cooled to improve the infrared stealth capability, the phase change cooling medium can be used to rapidly cool the front section side wall, the rear section side wall, and the side wall outer cover, thereby reducing the temperature of the front section side wall, the rear section side wall, and the side wall outer cover in a short time, avoiding the dual nozzle components from being eroded, and improving the infrared stealth capability of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is an external view of the dual-element nozzle of the engine provided in an embodiment of the present application;

[0036] Figure 2 is a cross-sectional view of a dual-element nozzle of an engine provided in an embodiment of the present application;

[0037] Figure 3 This is a side view of the engine dual nozzle provided by an embodiment of the present application without the side wall cover;

[0038] Figure 4 Schematic diagram of the structure of the dual nozzle portion of the engine provided in an embodiment of the present application;

[0039] Figure 5 2. It is a cross-sectional schematic diagram of a phase-change cooling medium jet tube provided in an embodiment of the present application having a jet hole;

[0040] in:

[0041] 1-circular rotating square section; 2-convergent section; 3-expanding section; 4-external adjustment plate; 5-front section side wall; 6-rear section side wall; 7-side wall outer cover; 8-phase change cooling medium jet tube; 9-partition plate; 10-gasket; 11-connecting flange; 12-sealing gasket; 13-bolt; 14-spring washer;

[0042] A-cooling air holes;

[0043] B-cooling exhaust hole;

[0044] C-cooling connecting hole;

[0045] D-rear exhaust slit;

[0046] E-air film hole;

[0047] F-jet hole.

[0048] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0049] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0050] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0051] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0052] The following is combined with Figures 1 to 5 This application is described in further detail.

[0053] An engine dual nozzle, comprising:

[0054] The circular rotating square section 1 has a front end connected to the rear end of the engine, and the outer wall of the rear end has a connecting edge;

[0055] The two convergent sections 2 have front ends hinged to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section 1. The connecting edges of the two opposite side walls at the rear end of the circular rotating square section 1 are provided with cooling air ducting holes A.

[0056] Two expansion sections 3, the front ends of which are hinged to the rear ends of the two convergence sections 2;

[0057] Two outer adjustment plates 4 are located outside the two convergent sections 2 and the expansion section 3, with their front ends hinged to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section 1. The rear end side walls are provided with a plurality of cooling exhaust holes B;

[0058] The front ends of the two front side walls 5 are connected to the connecting edges of the other two opposite side walls at the rear end of the circular rotating square section 1. The two opposite side walls at the rear end of the circular rotating square section 1 have clearance holes. A cooling air bleed cavity is formed between the two front side walls 5 and the two convergent sections 2, the expansion section 3, and the outer adjustment plate 4. A plurality of cooling communication holes C are distributed on the cooling air bleed cavity. The cooling air bleed cavity connects the cooling air bleed holes A, the cooling exhaust holes B, and the cooling communication holes C.

[0059] The two rear side walls 6 have front ends connected to the rear ends of the two front side walls 5, forming a rearward exhaust gap D between the two rear ends of the front side walls 5, and a plurality of air film holes E on the wall surface;

[0060] Two side wall covers 7 are located outside the two front side walls 5 and the rear side walls 6, with their front ends correspondingly connected to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section 1, and connected to the two front side walls 5 and the rear side walls 6 along the edges, forming a cooling exhaust cavity between the two front side walls 5 and the rear side walls 6; the cooling exhaust cavity is connected to each cooling communication hole C, the rear exhaust slit D, and the air film hole E;

[0061] One end of the two phase-change cooling medium jet tubes 8 passes through the two clearance holes and extends into the cooling exhaust cavity. The side wall of the portion extending into the cooling exhaust cavity has multiple jet holes F distributed along the axial direction.

[0062] For the engine dual nozzle disclosed in the above embodiment, technical personnel in the field can understand that the high-temperature gas in the aircraft engine can be discharged through the channel formed by the circular square section 1, the convergent section 2, the expansion section 3, the front section side wall 5, and the rear section side wall 6, and the cooling air bleed hole A can be used to introduce low-temperature gas into the cooling air bleed cavity. Part of the low-temperature gas can be discharged through the cooling exhaust hole B. This part of the low-temperature gas can cool the convergent section 2, the expansion section 3, and the outer adjustment plate 4 along the way. Another part of the low-temperature gas can enter the cooling exhaust cavity through the cooling connecting hole C, and then be discharged through the rear exhaust slit D and its air film hole E, forming an air film on the inner side of the rear section side wall 6. This part of the low-temperature gas can cool the front section side wall 5, the rear section side wall 6, and the side wall outer cover 7 along the way.

[0063] As for the engine dual nozzle disclosed in the above embodiment, those skilled in the art can understand that its design introduces external low-temperature gas to cool the internal and external components such as the convergent section 2, the expansion section 3, the outer adjustment plate 4, the front side wall 5, the rear side wall 6, and the side wall cover 7 along the way. The low-temperature gas used can come from the engine compartment or the external ram air. The cooling effect on the internal and external components can be guaranteed by controlling the flow rate of the low-temperature gas, and the infrared radiation characteristics of the internal and external components can be effectively suppressed to ensure the infrared stealth performance of the engine, and to avoid the internal components from being ablated and the external components from being deformed and warped, and there is no need to occupy additional external airflow.

[0064] As for the engine dual nozzle disclosed in the above embodiment, it can be understood by those skilled in the art that when the engine is in a high operating condition or needs to be rapidly cooled to enhance the infrared stealth capability, a phase-change cooling medium, such as liquid CO2, can be introduced into the phase-change cooling medium jet tube 8. The phase-change cooling medium can be sprayed into the cooling exhaust cavity through the jet hole F, and absorbs heat in the form of phase change to cool the front side wall 5, the rear side wall 6, and the side wall outer cover 7. The heat is then discharged through the rear exhaust slit D and its air film hole E to form an air film on the inner side of the rear side wall 6, thereby achieving rapid cooling of the front side wall 5, the rear side wall 6, and the side wall outer cover 7, reducing the temperature of the front side wall 5, the rear side wall 6, and the side wall outer cover 7 in a short time, avoiding the erosion of the dual nozzle components, and enhancing the infrared stealth capability of the engine.

[0065] The engine dual nozzle disclosed in the above embodiment, wherein the connection relationship between the circular rotating square section 1, the convergent section 2, the expansion section 3, and the outer adjustment plate 4 and its specific structural design, can be specifically referred to CN113107706, and no further detailed description is given here.

[0066] In some optional embodiments, in the above-mentioned engine dual nozzle, the rear ends of the two expansion sections 3 and the outer adjustment piece 4 are in a pointed cone shape, and the cooling exhaust holes B are distributed along the rear end edges of the two expansion sections 3 and the outer adjustment piece 4. The two front side walls 5, the rear side wall 6, and the side wall cover 7 are V-shaped as a whole, and the rear exhaust gap D is in a rearward-expanding V-shape to ensure the aerodynamic performance of the engine dual nozzle, and to achieve better cooling effect and better radar stealth performance.

[0067] In some optional embodiments, in the above-mentioned engine dual nozzle, the flow area of ​​the two cooling air ducts A is 1 to 2 times the flow area of ​​each cooling exhaust hole B and the cooling connecting hole C, and the flow area of ​​each cooling connecting hole C is 1 to 2 times the flow area of ​​the two rear exhaust slits D. Two phase-change cooling medium jet tubes 8 are extended into one end of the cooling exhaust cavity for sealing, and the flow area is 1.75 to 2 times the area of ​​the jet hole F thereon, so as to ensure the supply capacity of low-temperature airflow and phase-change cooling medium, and ensure the cooling effect on the engine dual nozzle components.

[0068] In some optional embodiments, in the above-mentioned engine dual nozzle, the two outer adjustment plates 4 converge inward, so that the cooling gas discharged through each cooling exhaust hole B converges inward, can cover and mix with the high-temperature gas discharged from the aircraft engine dual nozzle, so as to reduce noise, reduce exhaust temperature, and enhance stealth effect.

[0069] In some optional embodiments, in the above-mentioned engine dual nozzle, the number of jet holes F on each of the two phase-change cooling medium jet tubes 8 is an odd number greater than three, and is oriented towards the two rear side walls 6 or the side wall outer cover 7, with the angle between the jet hole F and the rear side wall 6 or the side wall outer cover 7 not exceeding 90°, and the middle jet hole F is perpendicular to the rear side wall 6 or the side wall outer cover 7, so that the phase-change cooling medium ejected through the jet hole F can efficiently impact the rear side wall 6 and the side wall outer cover 7, thereby ensuring the cooling effect on the rear side wall 6 and the side wall outer cover 7.

[0070] In some optional embodiments, the above-mentioned engine dual nozzle further includes:

[0071] Two partitions 9 are provided in the two cooling exhaust cavities to divide the cooling exhaust cavities into a front cooling exhaust cavity and a rear cooling exhaust cavity corresponding to the front side wall 5 and the rear side wall 6. The front cooling exhaust cavity is connected to each cooling communication hole C and the rear exhaust slit D; the rear cooling exhaust cavity is connected to each air film hole E.

[0072] Two phase-change cooling medium jet tubes 8 are arranged through the partition 9, and the upper jet holes F are partially located in the front cooling exhaust cavity. The phase-change cooling medium ejected through this part of the jet holes F enters the front cooling exhaust cavity and is discharged through the rear exhaust gap D after phase change. The other part is located in the rear cooling exhaust cavity. The phase-change cooling medium ejected through this part of the jet holes F enters the rear cooling exhaust cavity and is discharged through the air film hole E after phase change. The distribution density of the jet holes F located in the rear cooling exhaust cavity is greater than the distribution density of the jet holes F located in the front cooling exhaust cavity, so that the cooling effect on the front side wall 5 and the rear side wall 6 is uniform.

[0073] In some optional embodiments, the above-mentioned engine dual nozzle further includes:

[0074] Two gaskets 10 are sleeved on the outer periphery of the two phase-change cooling medium jet tubes 8 and welded to the outer sides of the connecting edges of the two opposite side walls;

[0075] The two connecting flanges 11 are sleeved on the two phase change cooling medium jet tubes 8, and are centered and positioned with the stoppers between the two gaskets 10, and a sealing gasket 12 is arranged therebetween. The two gaskets 10 are connected by bolts 13, and a spring washer 14 is arranged between the head of the bolt 13 and the connecting flange 11.

[0076] In some optional embodiments, in the above-mentioned engine dual nozzle, the phase change cooling medium jet tubes 8 and their corresponding components are in two groups corresponding to the two cooling exhaust cavities, with each group consisting of two.

[0077] The engine dual nozzle disclosed in the above embodiment can realize active on-demand control of the introduction of phase change cooling medium flow. The phase change cooling medium flow can be used on demand according to the actual scenario requirements. For example, during escape, it can be actively controlled to be turned on or increased in flow. The conventional cruising state can be adjusted to a moderate flow state or not used. The phase change cooling medium can specifically be supercritical carbon dioxide (-58.5 degrees Celsius) or liquid nitrogen (-196 degrees Celsius).

[0078] In the engine dual nozzle disclosed in the above embodiment, the cooling medium flows out from the holes on the nozzle cover and the side wall of the nozzle, and can be mixed with the high-temperature mainstream. In particular, it is discharged from the holes on the nozzle cover. While being discharged to the high-temperature mainstream, it also draws in external air, which can enhance heat exchange with the high-temperature mainstream and reduce the length of the high-temperature core area of ​​the exhaust mainstream behind the nozzle, thereby effectively reducing the infrared radiation intensity of the jet.

[0079] The various 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 between the various embodiments can be referred to in detail.

[0080] So far, the technical solution of the present 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 the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An engine dual nozzle, characterized in that: include: The circular rotating square section (1) has a front end connected to the rear end of the engine, and an outer wall of the rear end has a connecting edge; The two convergent sections (2) have front ends hinged to the connecting edges of two opposite side walls at the rear end of the circular rotating square section (1), and the connecting edges of the two opposite side walls at the rear end of the circular rotating square section (1) are provided with cooling air ducting holes (A); Two expansion sections (3), the front ends of which are hinged to the rear ends of the two convergence sections (2); Two outer adjustment plates (4) are located outside the two convergent sections (2) and the expansion section (3), and their front ends are hinged to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section (1), and a plurality of cooling exhaust holes (B) are distributed on the rear end side wall; The front ends of the two front section side walls (5) are connected to the connecting edges of the other two opposite side walls at the rear end of the circular rotating square section (1), and the two opposite side walls at the rear end of the circular rotating square section (1) are provided with clearance holes; a cooling air duct cavity is formed between the two front section side walls (5) and the two convergent sections (2), the expansion section (3), and the outer adjustment plate (4), and a plurality of cooling connecting holes (C) are distributed on the cooling air duct cavity; the cooling air duct cavity is connected to the cooling air duct holes (A), the cooling exhaust holes (B), and the cooling connecting holes (C); The two rear side walls (6) have front ends connected to the rear ends of the two front side walls (5), and a rearward exhaust slit (D) is formed between the two rear ends of the front side walls (5), and a plurality of air film holes (E) are provided on the wall surfaces; Two side wall covers (7) are located outside the two front side walls (5) and the rear side walls (6), with the front ends correspondingly connected to the connecting edges of the two opposite side walls at the rear end of the circular rotating square section (1), and connected to the two front side walls (5) and the rear side walls (6) along the edges, forming a cooling exhaust cavity between the two front side walls (5) and the rear side walls (6); the cooling exhaust cavity is connected to each cooling connecting hole (C), the rear exhaust slit (D), and the air film hole (E); Two phase-change cooling medium jet tubes (8) have one end extending through two clearance holes into the cooling exhaust cavity, and the side wall of the portion extending into the cooling exhaust cavity has a plurality of jet holes (F) distributed along the axial direction.

2. The engine dual nozzle according to claim 1, characterized in that: The rear ends of the two expansion sections (3) and the outer adjustment piece (4) are in a pointed cone shape; The cooling exhaust holes (B) are distributed along the two expansion sections (3) and the rear end edges of the outer adjustment plate (4); The two front side walls (5), the rear side wall (6), and the side wall outer cover (7) are V-shaped as a whole; The rear exhaust slit (D) is in a V-shape that expands rearward.

3. The engine dual nozzle according to claim 1, characterized in that: The flow area of ​​the two cooling air holes (A) is 1 to 2 times the flow area of ​​each cooling exhaust hole (B) and cooling connecting hole (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); Two phase-change cooling medium jet tubes (8) extend into one end of the cooling exhaust cavity and are sealed, and the flow area is 1.75 to 2 times the area of ​​the jet hole (F) thereon.

4. The engine dual nozzle according to claim 1, characterized in that: The two outer adjustment pieces (4) converge inwards.

5. The engine dual nozzle according to claim 1, characterized in that: The number of the jet holes (F) at each location on the two phase-change cooling medium jet tubes (8) is an odd number greater than three, and is oriented toward the two rear side walls (6) or the side wall outer cover (7), with the included angle between the jet holes (F) and the rear side walls (6) or the side wall outer cover (7) not exceeding 90°, and the jet hole (F) located in the middle is perpendicular to the rear side walls (6) or the side wall outer cover (7).

6. The engine dual nozzle according to claim 1, characterized in that: Also includes: Two partitions (9) are provided in the two cooling exhaust cavities to divide the cooling exhaust cavities into a front cooling exhaust cavity and a rear cooling exhaust cavity corresponding to the front side wall (5) and the rear side wall (6), wherein the front cooling exhaust cavity is connected to each cooling connecting hole (C) and the rear exhaust slit (D); and the rear cooling exhaust cavity is connected to each air film hole (E); Two phase-change cooling medium jet tubes (8) are arranged through the partition (9), and the jet holes (F) thereon are partially located in the front cooling exhaust cavity and partially located in the rear cooling exhaust cavity, and the distribution density of the jet holes (F) located in the rear cooling exhaust cavity is greater than the distribution density of the jet holes (F) located in the front cooling exhaust cavity.

7. The engine dual nozzle according to claim 1, characterized in that: Also includes: Two gaskets (10) are sleeved on the outer peripheries of the two phase-change cooling medium jet tubes (8) and welded to the outer sides of the connecting edges of the two corresponding opposite side walls; Two connecting flanges (11) are sleeved on two phase-change cooling medium jet tubes (8), and are centered and positioned between the stoppers of the two gaskets (10), and a sealing gasket (12) is arranged therebetween. The two gaskets (10) are connected via bolts (13), and a spring washer (14) is arranged between the head of the bolt (13) and the connecting flange (11).

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