CN116641809A - An engine binary nozzle - Google Patents

Abstract

The application belongs to the field of design of engine two-dimensional spray pipes, and particularly relates to an engine two-dimensional spray pipe, which is designed to introduce external low-temperature gas to cool inner components and outer components such as a converging section, an expanding section, an outer regulating piece, a front section side wall, a rear Duan Cebi side wall outer cover and the like along the way, and can ensure the cooling effect of the inner components and the outer components by controlling the flow of the low-temperature gas, avoid the ablation of the inner components and the deformation and warping of the outer components, and avoid the problem of extra occupation of external air flow.

Description

A binary nozzle for an engine

technical field

The application belongs to the field of engine binary nozzle design, and in particular relates to an engine binary nozzle.

Background technique

The binary nozzle of the engine is installed at the end of the engine, and the vector adjustment is carried out by using the contraction and expansion movement of the internal components such as the convergence section and the expansion section, and the external components such as the external adjustment piece and the side wall cover are designed to protect the internal components from being directly damaged by external forces. The exterior is rectified to reduce rear body drag.

The binary nozzle of the engine is affected by the high-temperature airflow and bears extremely high temperature loads. Its components are easily ablated and have obvious infrared radiation characteristics. For this, at present, the external airflow of the engine is mostly used to cool the components of the binary nozzle. Reduce the temperature of the binary nozzle components, avoid the ablation of the binary nozzle components, and suppress the infrared radiation characteristics to improve the infrared stealth ability. However, the external airflow also needs to be used to cool and cool other necessary high-temperature components. For The cooling capacity provided by the binary nozzle is limited, and cannot well meet the cooling requirements of the binary nozzle.

In view of the existence of above-mentioned technical defect, propose this application.

It should be noted that the disclosure of the above background technical content is only used to assist in understanding the inventive concepts and technical solutions of the present invention, and it does not necessarily belong to the prior art of this application. In the case that it has been disclosed on the date of publication, the above background technology should not be used to evaluate the novelty and inventiveness of this application.

Contents of the invention

The purpose of this application is to provide a binary nozzle for an engine to overcome or alleviate at least one known technical defect.

The technical scheme of the application is:

A binary nozzle for an engine, comprising:

The circular turning square section, the front end is connected to the rear end of the engine, and the outer wall of the rear end has a connecting edge;

Two converging sections, the front end is hinged on the connecting edge of the two opposite side walls at the rear end of the circular turning square section, and the connecting edge of the two opposite side walls at the rear end of the circular turning square section has cooling air holes;

Two expansion sections, the front end is hinged at the rear end of the two convergence sections;

Two external regulators are located on the outside of the two converging sections and the expansion section, and the front ends are correspondingly hinged on the connecting edge of the two opposite side walls at the back end of the circular turning square section, and a plurality of cooling exhaust holes are distributed on the side wall at the back end;

The two front section side walls, the front end is connected to the connecting edge of the other two opposite side walls at the rear end of the round turning square section, and the two opposite side walls at the back end of the round turning square section have relief holes; the two front section side walls are connected to the A cooling air-introduction cavity is formed between the two converging sections, the expansion section, and the outer regulating piece, and a plurality of cooling communication holes are distributed on it; the cooling air-induction cavity is connected to each cooling air-induction hole, cooling exhaust hole, and cooling communication hole;

The two rear side walls, the front ends are connected to the rear ends of the two front side walls, and a rearward exhaust slot is formed between the rear ends of the two front side walls, and there are multiple air film holes on the wall surface;

Two side wall covers are located on the outside of the two front side walls and the rear side wall, and the front end is correspondingly connected to the connecting edge of the two opposite side walls at the rear end of the round and square section, and is connected to the two front side walls and the rear side. The walls are connected along the edge, forming a cooling exhaust chamber with the two front side walls and the rear side wall; the cooling exhaust chamber is connected to each cooling communication hole, rearward exhaust slot, and air film hole;

One end of the two phase-change cooling medium jet tubes extends into the cooling exhaust chamber through the two relief holes, and a part of the side wall extending into the cooling exhaust chamber has a plurality of jet holes distributed along the axial direction.

According to at least one embodiment of the present application, in the binary nozzle of the above-mentioned engine, the two expansion sections and the rear end of the outer regulating plate are tapered;

Each cooling exhaust hole is distributed along the two expansion sections and the rear end edge of the outer regulating plate;

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

The rear exhaust slit is V-shaped with rearward expansion.

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

The flow area of each cooling communication hole is 1 to 2 times the flow area of the two rear exhaust slots;

Two phase-change cooling medium jet tubes extend into one end of the cooling exhaust chamber and are sealed, and the flow area is 1.75-2 times the area of the upper jet hole.

According to at least one embodiment of the present application, in the binary nozzle of the above-mentioned engine, the two outer regulating fins converge inwardly.

According to at least one embodiment of the present application, in the binary nozzle of the above-mentioned engine, the number of jet holes on the two phase-change cooling medium jet tubes is an odd number greater than three, and they are directed towards the two rear section side walls or sides. The angle between the wall cover and the rear section side wall or the side wall cover is not more than 90°, and the jet hole in the middle is perpendicular to the rear section side wall or the side wall cover.

According to at least one embodiment of the present application, the above-mentioned engine binary nozzle also includes:

Two partitions are arranged in the two cooling exhaust chambers, and divide the cooling exhaust chamber into a front cooling exhaust chamber and a rear cooling exhaust chamber corresponding to the front section side wall and the rear section side wall, wherein the front cooling row The air cavity is connected to each cooling communication hole and the rear exhaust slot; the rear cooling exhaust cavity is connected to each air film hole;

Two phase-change cooling medium jet tubes are set through the partition, and the upper jet holes are partly located in the front cooling exhaust cavity, and partly located in the rear cooling exhaust cavity, and the distribution density of the jet holes in the rear cooling exhaust cavity is higher than that in the front cooling exhaust cavity. The distribution density of jet holes in the air cavity.

According to at least one embodiment of the present application, the above-mentioned engine binary nozzle also includes:

Two backing rings are sleeved on the outer peripheries of the two phase-change cooling medium jet tubes, and welded on the outer sides corresponding to the connecting edges of the two opposite side walls;

The two connecting flanges are sleeved on the two phase-change cooling medium jet pipes, centered and positioned with the joints between the two backing rings, and a sealing gasket is arranged between them, and bolts are passed between the two backing rings For connection, a spring washer is set between the head of the bolt and the connecting flange.

According to at least one embodiment of the present application, in the binary nozzle of the above-mentioned engine, there are two groups of phase-change cooling medium jet pipes and corresponding components corresponding to the two cooling exhaust chambers, and each group is two.

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

Provide a binary nozzle of an engine, which is designed to introduce external low-temperature air to cool the internal and external components such as the convergent section, the expansion section, the outer regulating plate, the front section side wall, the rear section side wall, and the side wall cover along the way, which can be passed Control the flow of low-temperature gas to ensure the cooling effect of internal components and external components, physical performance, and avoid ablation of internal components, deformation and warping of external components, and no need to occupy additional external airflow. In addition, in When the engine is in a heavy working condition or needs to be cooled rapidly to reduce the infrared stealth ability, the phase change cooling medium can be used to rapidly cool the front section side wall, rear section side wall, and side wall cover, and reduce the front section side wall in a short time. The temperature of the wall, the rear section side wall, and the side wall cover can prevent the binary nozzle components from being ablated, and improve the infrared stealth ability of the engine.

Description of drawings

Fig. 1 is the external view of the binary nozzle of the engine provided by the embodiment of the present application;

Fig. 2 is the sectional view of the binary nozzle of the engine provided by the embodiment of the present application;

Fig. 3 is a side view diagram of the binary nozzle of the engine provided by the embodiment of the present application without the side wall cover;

Fig. 4 is a schematic diagram of the partial structure of the binary nozzle of the engine provided by the embodiment of the present application;

Fig. 5 is a schematic cross-sectional view of a phase-change cooling medium jet tube provided in an embodiment of the present application at a jet hole;

in:

1-Circle to square section; 2-Convergence section; 3-Expansion section; 4-External adjustment piece; 5-Front section side wall; 6-Rear section side wall; 7-Side wall outer cover; ;9-partition plate; 10-gasket ring; 11-connecting flange; 12-gasket; 13-bolt; 14-spring washer;

A-cooling air hole;

B-cooling vent;

C-cooling through hole;

D-rear exhaust slot;

E-air film hole;

F- jet hole.

In order to better illustrate this embodiment, certain components in the drawings are omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only for illustrative purposes and should not be construed as limiting the application.

Detailed ways

In order to make the technical solution of the present application and its advantages clearer, the technical solution of the present application will be further clearly and completely described in detail below in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only part of the application Examples are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other relevant parts can refer to the general design. In the case of no conflict, the embodiments in the application and the technologies in the embodiments Features can be combined with each other to obtain new embodiments.

In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the application shall have the usual meanings understood by those skilled in the art to which the application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" used in the description of this application are used only To indicate relative orientation or positional relationship, not to imply that the device or component must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the described object changes, its relative positional relationship may also change accordingly , and therefore cannot be construed as limiting the application. The terms "first", "second", "third" and similar terms used in the description of this application are used for descriptive purposes only to distinguish different components, and should not be understood as indicating or implying relative importance. Words such as "a", "an" or "the" used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as there is at least one. The words "comprising" or "comprising" and other similar words used in the description of the present application mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

In addition, it should be noted that, unless otherwise specified and limited, words such as "installation", "connection" and "connection" used in the description of this application should be interpreted in a broad sense, for example, the connection can be a fixed The connection can also be detachable or integrated; it can be mechanical or electrical; it can be direct or indirect through an intermediary; it can also be the internal communication of two components. A skilled person can understand its specific meaning in this application according to specific circumstances.

The present application will be described in further detail below in conjunction with accompanying drawings 1 to 5 .

A binary nozzle for an engine, comprising:

Circle section 1, the front end is connected to the rear end of the engine, and the outer wall of the rear end has a connecting edge;

Two converging sections 2, the front ends of which are hinged on the connecting edges of the two opposite side walls at the rear end of the circular turning square section 1, and cooling air-introduction holes A are provided on the connecting edges of the two opposite side walls at the rear end of the circular turning square section 1;

Two expansion sections 3, the front ends of which are hinged at the rear ends of the two convergence sections 2;

The two outer regulating pieces 4 are located on the outer sides of the two converging sections 2 and the expanding sections 3, and the front ends are correspondingly hinged on the connecting edge of the two opposite side walls at the rear end of the circular turning square section 1, and a plurality of cooling rows are distributed on the rear end side walls stomata B;

Two front section side walls 5, the front end is connected on the connecting edge of the other two opposite side walls at the rear end of the circle turning square section 1, and the two opposite side walls at the back end of the circle turning square section 1 have relief holes; the two front sections A cooling air chamber is formed between the side wall 5 and the two converging sections 2, the expansion section 3, and the outer regulating piece 4, and a plurality of cooling communication holes C are distributed thereon; the cooling air chamber is connected to each cooling air hole A, cooling row Air hole B, cooling communication hole C;

The two rear side walls 6, the front ends are connected to the rear ends of the two front side walls 5, and the rearward exhaust seam D is formed between the rear ends of the two front side walls 5, and there are a plurality of air film holes E on the wall surface;

Two side wall covers 7 are located on the outsides of the two front side walls 5 and the rear side walls 6. 5. The rear section side wall 6 is connected along the edge, forming a cooling exhaust cavity with the two front section side walls 5 and the rear section side wall 6; the cooling exhaust cavity is connected to each cooling communication hole C, the rear exhaust slot D, Air film hole E;

One end of the two phase-change cooling medium jet tubes 8 extends into the cooling exhaust cavity through two relief holes, and the part of the side wall extending into the cooling exhaust cavity has a plurality of jet holes F distributed along the axial direction.

For the engine binary nozzle disclosed in the above embodiments, those skilled in the art can understand that the high-temperature gas in the aero-engine can pass through the circle section 1, the convergence section 2, the expansion section 3, the front section side wall 5, and the rear section The channel formed by the side wall 6 is discharged, and the cooling air-introduction hole A can be used to introduce low-temperature air into the cooling air-introduction chamber, and part of the low-temperature air can be discharged through the cooling exhaust hole B. 3. The outer regulating piece 4 is used for cooling, and another part of the low-temperature air can enter the cooling exhaust chamber through the cooling communication hole C, and then be discharged through the rearward exhaust slot D and its air film hole E, and is on the inner side of the rear side wall 6 An air film is formed, and this part of low-temperature air can cool the front side wall 5, the rear side wall 6, and the side wall cover 7 along the way.

For the engine binary nozzle disclosed in the above embodiment, those skilled in the art can understand that its design introduces the external low-temperature gas pair converging section 2, expanding section 3, external regulating piece 4, front section side wall 5, and rear section side wall 6. The internal components and external components such as the side wall cover 7 are cooled along the process. The low-temperature air used can come from the engine compartment or external ram air. By controlling the flow of low-temperature air, the cooling effect on the internal components and external components can be ensured, which can Effectively suppress the infrared radiation characteristics of internal and external components, ensure the infrared stealth performance of the engine, and avoid ablation of internal components, deformation and warping of external components, and no need to occupy additional external airflow.

For the binary nozzle of the engine disclosed in the above embodiment, those skilled in the art can understand that, when the engine is in a large working condition or needs to be rapidly cooled to improve the infrared stealth ability, the phase change cooling medium jet pipe 8 A phase-change cooling medium is introduced inside, for example, it can be liquid CO2, and the phase-change cooling medium can be sprayed into the cooling exhaust cavity through the jet hole F to absorb heat in the form of phase change, and the front section side wall 5 and the rear section side wall 6. The side wall cover 7 is cooled, and then it is discharged through the rear exhaust slot D and its air film hole E, forming an air film on the inner side of the rear side wall 6, which can realize the front side wall 5 and the rear side wall. 6. The rapid cooling of the side wall cover 7 reduces the temperature of the front section side wall 5, the rear section side wall 6, and the side wall cover 7 in a short time, avoiding the ablation of the binary nozzle components, and improving the infrared stealth ability of the engine.

For the engine binary nozzle disclosed in the above-mentioned embodiments, the connection relationship between the circular turning square section 1, the converging section 2, the expanding section 3, and the outer regulating piece 4 and its specific structural design can be referred to CN113107706, which will not be described here. Let's give a more detailed explanation.

In some optional embodiments, in the binary nozzle of the above-mentioned engine, the rear ends of the two expansion sections 3 and the outer adjustment piece 4 are tapered, and each cooling exhaust hole B is adjusted along the two expansion sections 3 and the outer adjustment plate. The edge of the rear end of sheet 4 is distributed, 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 seam D is a V-shape that expands backward to ensure that the engine binary nozzle Excellent aerodynamic performance, better cooling effect, and better radar stealth performance.

In some optional embodiments, in the binary nozzle of the above-mentioned engine, the flow area of the two cooling air intake holes A is 1 to 2 times the flow area of each cooling exhaust hole B and cooling communication hole C. The flow area of the communication hole C is 1 to 2 times the flow area of the two backward exhaust slots D, and the two phase-change cooling medium jet tubes 8 extend into one end of the cooling exhaust cavity to block, and the flow area is above The area of jet hole F is 1.75 to 2 times to ensure the supply capacity of low-temperature airflow and phase-change cooling medium, and to ensure the cooling effect on the binary nozzle components of the engine.

In some optional embodiments, in the binary nozzle of the above-mentioned engine, the two outer regulating fins 4 converge inward, so that the cooling air discharged through each cooling exhaust hole B converges inward, and can be wrapped and connected with The aero-engine binary nozzle discharges high-temperature gas for mixing to reduce noise, reduce exhaust temperature, and improve stealth effect.

In some optional embodiments, in the above-mentioned engine binary nozzle, the number of jet holes F on the two phase-change cooling medium jet tubes 8 is an odd number greater than three, and they are directed towards the two rear section side walls. 6 or the side wall cover 7, and the angle between the rear section side wall 6 or the side wall cover 7 is not more than 90°, and the jet hole F in the middle is perpendicular to the rear section side wall 6 or the side wall cover 7, so that the jet flow The phase-change cooling medium ejected from the hole F can efficiently impact the rear side wall 6 and the side wall cover 7 to ensure the cooling effect on the rear side wall 6 and the side wall cover 7 .

In some optional embodiments, the above-mentioned engine binary nozzle also includes:

Two partitions 9 are arranged in the two cooling exhaust chambers, and divide the cooling exhaust chamber into a front cooling exhaust chamber and a rear cooling exhaust chamber corresponding to the front section side wall 5 and the rear section side wall 6, wherein, The front cooling exhaust cavity is connected to each cooling communication hole C and the rear exhaust slot D; 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 plate 9, and part of the upper jet hole F is located in the front cooling exhaust chamber, and the phase-change cooling medium ejected through this part of the jet hole F enters the front cooling exhaust chamber. After the phase change, it is discharged through the rear exhaust slot D, and part of it is located in the rear cooling exhaust chamber. The phase change cooling medium sprayed out through the jet hole F of this part enters the rear cooling exhaust chamber, and is discharged through the air film hole E after the phase change. The distribution density of jet holes F in the rear cooling exhaust cavity is greater than that 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.

In some optional embodiments, the above-mentioned engine binary nozzle also includes:

Two backing rings 10 are sleeved on the outer circumference of the two phase-change cooling medium jet tubes 8 and welded on the outer sides corresponding to the connecting sides of the two opposite side walls;

The two connecting flanges 11 are sleeved on the two phase-change cooling medium jet pipes 8, centered and positioned between the two backing rings 10, and a sealing gasket 12 is arranged therebetween, and connected with the two backing rings 10 are connected by bolts 13, and a spring washer 14 is arranged between the heads of the bolts 13 and the connecting flange 11.

In some optional embodiments, in the binary nozzle of the engine mentioned above, there are two groups of phase-change cooling medium jet pipes 8 and their corresponding components corresponding to the two cooling exhaust chambers, and each group is two.

The binary nozzle of the engine disclosed in the above embodiments can realize active on-demand control of the flow of the phase-change cooling medium, and use the flow of the phase-change cooling medium on demand according to the actual scene requirements. If it is escaping, it can be actively controlled to use or increase the flow Use, conventional cruising state can be adjusted to a moderate flow state or not in use, wherein said phase change cooling medium can specifically use supercritical carbon dioxide (-58.5 degrees Celsius) or liquid nitrogen (-196 degrees Celsius).

In the binary nozzle of the engine disclosed in the above embodiments, the cooling medium flows out from the nozzle housing and the holes on the side wall of the nozzle, and can be mixed with the high-temperature main flow, especially discharged from the holes on the nozzle housing. At the same time, it will also engulf the outside air, which can enhance the 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.

Each embodiment in the description is described in a progressive manner, each embodiment focuses on the difference from other embodiments, and the same and similar parts of each embodiment can be referred to each other.

So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, without departing from the principle of the application Those skilled in the art can make equivalent changes or substitutions to the relevant technical features under the premise of the above-mentioned conditions, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims (7)

1. An engine two-way nozzle, comprising:

the round square section (1) is connected with the rear end of the engine, and the outer wall of the rear end is provided with a connecting edge;

the front ends of the two convergence sections (2) are hinged to the connecting edges of the two opposite side walls at the rear end of the round rotating square section (1), and the connecting edges of the two opposite side walls at the rear end of the round rotating square section (1) are provided with cooling air holes (A);

the front ends of the two expansion sections (3) are hinged to the rear ends of the two convergence sections (2);

the two outer adjusting pieces (4) are positioned outside the two converging sections (2) and the expanding section (3), the front ends of the two outer adjusting pieces are correspondingly hinged on the connecting edges of two opposite side walls of the rear end of the round rotating square section (1), and a plurality of cooling exhaust holes (B) are distributed on the side wall of the rear end;

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 round rotating square section (1), and the two opposite side walls at the rear end of the round rotating square section (1) are provided with abdicating holes; a cooling air introducing cavity is formed between the two front section side walls (5) and the two convergence sections (2), the expansion section (3) and the outer adjusting piece (4), and a plurality of cooling communication holes (C) are distributed on the cooling air introducing cavity; the cooling air introducing cavity is communicated with each cooling air introducing hole (A), the cooling air discharging hole (B) and the cooling communication hole (C);

the front ends of the two rear section side walls (6) are connected with the rear ends of the two front section side walls (5), a backward exhaust slot (D) is formed between the front ends of the two front section side walls (5), and a plurality of air film holes (E) are formed in the wall surfaces;

the two side wall outer covers (7) are positioned outside the two front section side walls (5) and the rear section side wall (6), the front ends are correspondingly connected to the connecting edges of the two opposite side walls at the rear end of the round rotating square section (1), and are connected with the two front section side walls (5) and the rear section side wall (6) along the edges, and a cooling exhaust cavity is formed between the two front section side walls (5) and the rear section side wall (6); the cooling exhaust cavity is communicated with each cooling communication hole (C), a backward exhaust slot (D) and a gas film hole (E);

and one end of the two phase-change cooling medium jet pipes (8) penetrates through the two abdicating holes to extend into the cooling exhaust cavity, and a part of the side wall extending into the cooling exhaust cavity is provided with a plurality of jet holes (F) distributed along the axial direction.

2. The engine two-way nozzle of claim 1, wherein,

the rear ends of the two expansion sections (3) and the outer adjusting piece (4) are pointed cone-shaped;

each cooling exhaust hole (B) is distributed along the rear edges of the two expansion sections (3) and the outer adjusting piece (4);

the two front section side walls (5), the rear section side wall (6) and the side wall outer cover (7) are integrally V-shaped;

the backward exhaust slot (D) is in a V shape expanding backward.

3. The engine two-way nozzle of claim 1, wherein,

the flow area of the two cooling air-introducing holes (A) is 1-2 times of the flow area of each cooling air-discharging hole (B) and cooling communication hole (C);

the flow area of each cooling communication hole (C) is 1-2 times of the flow area of the two backward exhaust slits (D);

one end of the two phase-change cooling medium jet pipes (8) extending into the cooling exhaust cavity is plugged, and the flow area is 1.75-2 times of the area of the jet hole (F) on the cooling exhaust cavity.

4. The engine two-way nozzle of claim 1, wherein,

the two outer adjusting sheets (4) are converged inwards.

5. The engine two-way nozzle of claim 1, wherein,

the number of jet holes (F) at each position on the two phase-change cooling medium jet pipes (8) is an odd number larger than three, the jet holes face to the two rear-section side walls (6) or the side wall outer covers (7), the included angle between the jet holes and the rear-section side walls (6) or the side wall outer covers (7) is not more than 90 degrees, and the jet holes (F) in the middle are perpendicular to the rear-section side walls (6) or the side wall outer covers (7).

6. The engine two-way nozzle of claim 1, wherein,

further comprises:

the two partition plates (9) are arranged in the two cooling exhaust chambers, and divide the cooling exhaust chambers into front cooling exhaust chambers and rear cooling exhaust chambers corresponding to the front section side wall (5) and the rear section side wall (6), wherein the front cooling exhaust chambers are communicated with the cooling communication holes (C) and the rear exhaust slots (D); the post-cooling exhaust cavity is communicated with each air film hole (E);

the two phase-change cooling medium jet pipes (8) penetrate through the partition plate (9), part of the upper jet holes (F) of the phase-change cooling medium jet pipes are located in the front cooling exhaust cavity, part of the upper jet holes are located in the rear cooling exhaust cavity, and the distribution density of the jet holes (F) located in the rear cooling exhaust cavity is larger than that of the jet holes (F) located in the front cooling exhaust cavity.

7. The engine two-way nozzle of claim 1, wherein,

further comprises:

the two backing rings (10) are sleeved on the peripheries of the two phase-change cooling medium jet pipes (8) and welded on the outer sides of the connecting edges of the two opposite side walls;

the two connecting flanges (11) are sleeved on the two phase-change cooling medium jet pipes (8), are centered and positioned with the rabbets between the two backing rings (10), are provided with sealing gaskets (12) therebetween, are connected with the two backing rings (10) through bolts (13), and are provided with spring washers (14) between the heads of the bolts (13) and the connecting flanges (11).