A pre-cooling structure of inlet jet for an air-breathing hypersonic vehicle engine intake

Abstract

The present application relates to a jet pre-cooling structure at the inlet of a hypersonic aircraft engine intake, comprising: an intake; a jet strut, in a leaf shape, supported at the inlet part of the intake, having a jet cavity and an anti-icing cavity therein, and having a jet orifice communicating with the jet cavity and an anti-icing air intake orifice communicating with the anti-icing cavity on its side wall, one end of which exposes from the side wall of the intake, and this end has an opening communicating with the jet cavity and the anti-icing cavity; a cover plate, connected to the jet strut to block the opening, and having a pre-cooling liquid inflow hole communicating with the jet cavity and an anti-icing air inlet hole communicating with the anti-icing cavity thereon; a pre-cooling liquid nozzle, installed in the pre-cooling liquid inflow hole; an anti-icing air nozzle, installed in the anti-icing air inlet hole; a jet pipe, arranged in the jet cavity, one end of which is blocked and the other end is communicated with the pre-cooling liquid inflow hole, and having jet orifices on its side wall; a jet nozzle, installed in the jet orifices; a spacer, arranged in the jet cavity, abutting against the jet pipe; a heat-insulating and vibration-proof pad, filled in the jet cavity.

Description

Technical Field

[0001] This application belongs to the technical field of inlet jet pre-cooling design for hypersonic aircraft engines, and particularly relates to a hypersonic aircraft inlet jet pre-cooling structure. Background Art

[0002] When a hypersonic aircraft flies at a high Mach number under high-altitude conditions, the total temperature of the oncoming flow at the engine inlet significantly rises, causing extremely high temperature loads on each cross-section of the engine and easily resulting in damage to engine components. Therefore, jet pre-cooling technology has been developed. By spraying pre-cooling liquid at the engine inlet, the oncoming flow at the engine inlet is pre-cooled to protect the aero-engine components from high-temperature damage.

[0003] Currently, when applying jet pre-cooling technology, a grid or rod-shaped structure is mostly set at the inlet of the hypersonic aircraft engine inlet to form connected liquid paths, and pre-cooling liquid is sprayed at the engine inlet. This technical solution has the following defects:

[0004] 1) The grid or rod-shaped structure forms connected liquid paths with low stiffness and weak damping, which are easily damaged by vibration during operation and have weak resistance to foreign object impact, unable to meet the installation requirements of hypersonic aircraft engines;

[0005] 2) It causes a large pressure loss to the oncoming flow of the hypersonic aircraft engine inlet, easily distorts the airflow at the inlet of the inlet, and affects the overall performance of the engine;

[0006] 3) When a hypersonic aircraft flies at a high Mach number under high-altitude conditions, before the pre-cooling liquid in the liquid path is ejected, it is easily heated by the oncoming flow of the engine inlet, affecting the jet pre-cooling effect;

[0007] 4) When a hypersonic aircraft flies at a low Mach number, the connected liquid paths formed by the grid or rod-shaped structure do not have an anti-icing function, and an additional anti-icing device needs to be designed for anti-icing. The number of components is large, the structural reliability is poor, and it is difficult to assemble.

[0008] In view of the existence of the above technical defects, this application is proposed.

[0009] It should be noted that the disclosure of the above background art 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 this patent application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background art should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0010] The purpose of this application is to provide a hypersonic aircraft engine inlet jet pre-cooling structure to overcome or mitigate at least one aspect of the known technical defects.

[0011] The technical solution of this application is as follows:

[0012] A jet pre-cooling structure at the inlet of a spaceplane engine inlet duct, comprising:

[0013] An inlet duct;

[0014] Jet support plates, in a leaf shape, supported at the inlet part of the inlet duct, having a jet cavity and an anti-icing cavity inside, with jet ports communicating with the jet cavity and anti-icing air intake holes communicating with the anti-icing cavity on its side walls, one end of which exposes from the side wall of the inlet duct, and this end has openings communicating with the jet cavity and the anti-icing cavity;

[0015] A cover plate, connected to the jet support plates, sealing the openings, having a pre-cooling liquid inflow hole communicating with the jet cavity and an anti-icing air inlet hole communicating with the anti-icing cavity on it;

[0016] A pre-cooling liquid nozzle, installed in the pre-cooling liquid inflow hole;

[0017] An anti-icing air nozzle, installed in the anti-icing air inlet hole;

[0018] A jet pipe, arranged in the jet cavity, one end of which is blocked, and the other end is communicated with the pre-cooling liquid inflow hole, and its side wall has jet holes;

[0019] A jet nozzle, installed in the jet holes;

[0020] A spacer block, arranged in the jet cavity, abutting against the jet pipe, so that the jet nozzle leaks out from the jet port;

[0021] A heat-insulating and vibration-proof pad, filled in the jet cavity.

[0022] According to at least one embodiment of this application, in the above jet pre-cooling structure at the inlet of the spaceplane engine inlet duct, both ends of the jet support plates have boss structures, which are respectively stuck in the clamping grooves opened on the side walls of the inlet part of the inlet duct.

[0023] According to at least one embodiment of this application, in the above jet pre-cooling structure at the inlet of the spaceplane engine inlet duct, the jet support plates are of split structure.

[0024] According to at least one embodiment of this application, in the above jet pre-cooling structure at the inlet of the spaceplane engine inlet duct, the anti-icing cavity and its anti-icing air intake holes are located at the leading edge part of the jet support plates;

[0025] The anti-icing air intake holes are inclined towards the trailing edge direction of the jet support plates.

[0026] According to at least one embodiment of this application, in the above jet pre-cooling structure at the inlet of the spaceplane engine inlet duct, one end of the opening of the jet support plates has a positioning groove;

[0027] The outer wall of one end of the jet pipe facing the cover plate has a positioning protrusion, which is stuck in the positioning groove.

[0028] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, the jet nozzle is a centrifugal nozzle.

[0029] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, the cross-section of the jet pipe is approximately rectangular;

[0030] The inlet jet pre-cooling structure of the aerospace plane engine further includes:

[0031] A jet nozzle mounting seat, which has opposite flanges, and the opposite clamping edges are clamped on the opposite edges on both sides of the jet pipe, and it has threaded holes communicating with the jet holes;

[0032] The jet nozzle is screwed into the threaded hole.

[0033] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, it further includes:

[0034] A gasket, which is placed between the jet nozzle and the jet nozzle mounting seat.

[0035] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, it further includes:

[0036] A spacer, which is placed between the jet support plate and the jet nozzle.

[0037] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, there are multiple limiting grooves in the jet cavity;

[0038] There are multiple jet pipes and their corresponding components and structures, and each jet pipe is arranged in a limiting groove.

[0039] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, the jet nozzles corresponding to each jet pipe are distributed on both sides facing the jet support plate.

[0040] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, there are multiple jet nozzles and their corresponding components and structures corresponding to each jet pipe, and the jet nozzles on each jet pipe are distributed along the axial direction of the jet support plate.

[0041] According to at least one embodiment of the present application, in the inlet jet pre-cooling structure of the aerospace plane engine described above, there are multiple anti-icing air intake holes, which are distributed along the axial direction on both sides of the jet support plate.

[0042] According to at least one embodiment of the present application, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, there are multiple jet splitter plates and their corresponding components and structures;

[0043] Each jet splitter plate is arranged and distributed radially at the inlet part of the inlet duct. Description of the Drawings

[0044] Figure 1 is a schematic diagram of the jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct provided by the embodiment of the present application;

[0045] Figure 2 is a partial schematic diagram of the jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct provided by the embodiment of the present application;

[0046] Figure 3 is Figure 2 a sectional view taken along the A-A direction of

[0047] Figure 4 is a schematic diagram of the jet pipe provided by the embodiment of the present application;

[0048] Figure 5 is a schematic diagram of the jet nozzle provided by the embodiment of the present application;

[0049] Figure 6 is a schematic diagram of the jet nozzle mounting seat provided by the embodiment of the present application;

[0050] Wherein:

[0051] 1 - Inlet duct; 2 - Jet splitter plate; 3 - Cover plate; 4 - Pre-cooling liquid nozzle; 5 - Anti-icing air nozzle; 6 - Jet pipe; 7 - Jet nozzle; 8 - Spacer block; 9 - Heat insulation and vibration damping pad; 10 - Jet nozzle mounting seat; 11 - Sealing gasket; 12 - Spacer.

[0052] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed Embodiments

[0053] To make the technical solutions of the present application and their advantages clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and 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 related parts can refer to the general design. Without conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0054] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or positional relationships, rather than implying that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. Therefore, it should not be construed as a limitation to this application. The terms "first", "second", "third", and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and should not be construed as indicating or implying relative importance. The similar words such as "a", "an", or "the" used in the description of this application should not be construed as an absolute limitation on the quantity but should be understood as meaning at least one. The similar words such as "comprising" or "including" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0055] In addition, it should be noted that, unless otherwise clearly specified and limited, the similar words such as "installed", "connected", and "joined" 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 or an indirect connection through an intermediate medium, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0056] The following will further elaborate on this application in conjunction with the Figures 1 to 6 accompanying drawings.

[0057] A pre-cooling structure of the inlet jet for a spaceplane engine intake duct, comprising:

[0058] The intake duct 1;

[0059] The jet strut 2, in a leaf shape, supported at the inlet part of the intake duct 1, having a jet cavity and an anti-icing cavity inside it, with a jet orifice communicating with the jet cavity and an anti-icing air intake hole communicating with the anti-icing cavity on its side wall. One end of it protrudes from the side wall of the intake duct 1, and this end has an opening communicating with the jet cavity and the anti-icing cavity;

[0060] The cover plate 3, connected to the jet strut 2, sealing the opening, having a pre-cooling liquid inlet hole communicating with the jet cavity and an anti-icing air inlet hole communicating with the anti-icing cavity on it;

[0061] The pre-cooling liquid nozzle 4, installed in the pre-cooling liquid inlet hole;

[0062] The anti-icing gas nozzle 5 is installed in the anti-icing gas inlet hole;

[0063] The jet pipe 6 is arranged in the jet cavity, one end is blocked, the other end is communicated with the pre-cooling liquid inflow hole, and its side wall has jet holes;

[0064] The jet nozzle 7 is installed in the jet hole;

[0065] The spacer 8 is arranged in the jet cavity, abuts against the jet pipe 6, and makes the jet nozzle 7 leak out from the jet port;

[0066] The heat-insulating and vibration-proof pad 9 is filled in the jet cavity.

[0067] For the jet pre-cooling structure at the inlet of the air-breathing hypersonic vehicle engine inlet disclosed in the above embodiments, those skilled in the art can understand that it integrates the pre-cooling function and its anti-icing function by using the jet strut 2, with a compact structure and convenient assembly. When the air-breathing hypersonic vehicle flies at a high Mach number under high-altitude conditions, pre-cooling liquid can be introduced into the jet pipe 6 through the pre-cooling liquid nozzle 4, and sprayed into the engine inlet through the jet nozzle 7 to pre-cool and cool down the oncoming flow at the engine inlet, protecting the components of the aero-engine from high-temperature damage. When the air-breathing hypersonic vehicle flies at a low Mach number, anti-icing gas can be introduced into the anti-icing cavity through the anti-icing gas nozzle 5 and discharged through the anti-icing air inlet holes, adhering to the surface of the jet strut 2 to achieve the anti-icing function.

[0068] For the jet pre-cooling structure at the inlet of the air-breathing hypersonic vehicle engine inlet disclosed in the above embodiments, those skilled in the art can also understand that it is supported by the jet strut 2 at the inlet part of the inlet duct 1 as a whole. The jet strut 2 is in a leaf shape, which can reduce the pressure loss of the oncoming flow of the air-breathing hypersonic vehicle engine inlet duct, avoid the distortion of the airflow at the inlet of the inlet duct, and thus ensure the overall performance of the engine. Moreover, it has sufficient stiffness, strength, and strong ability to resist foreign object damage, and is convenient for installation on the aircraft.

[0069] For the jet pre-cooling structure at the inlet of the air-breathing hypersonic vehicle engine inlet disclosed in the above embodiments, those skilled in the art can also understand that it is designed to fill the heat-insulating and vibration-proof pad 9 in the jet cavity. The anti-vibration and heat-insulating pad 9 can be made of lightweight, heat-insulating, and vibration-isolating materials, and its specific shape can be strip-shaped, which is suitable for being smoothly filled into the jet cavity. By filling the jet cavity with the anti-vibration and heat-insulating pad 9, on the one hand, it has a damping effect and can reduce the possibility of the overall structure being damaged by vibration. On the other hand, it has a heat-insulating effect and can cover the jet pipe 6 to avoid the pre-cooling liquid inside being heated by the oncoming flow of the engine inlet duct before spraying, affecting the jet pre-cooling effect.

[0070] Regarding the jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct disclosed in the above embodiments, those skilled in the art can also understand that its design is based on a spacer 8 provided in the jet cavity, which abuts against the jet pipe 6, causing the jet nozzle 7 to leak out from the jet orifice. The shape of the spacer 8 can be strip-shaped, so that it can smoothly extend into the jet cavity, abut against the jet pipe 6, and preferably fix the jet nozzle 7. When assembling this part of the structure, the following steps can be referred to:

[0071] Insert the jet pipe 6 together with the jet nozzle 7 thereon into the jet cavity;

[0072] Align the jet nozzle 7 with the jet orifice, and along the radial direction of the jet support plate 2, push the jet pipe 6 so that the jet nozzle 7 leaks out from the jet orifice;

[0073] Insert the spacer 8 into the jet cavity, abut against the jet pipe 6, and fix the position of the jet nozzle 7.

[0074] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, both ends of the jet support plate 2 have boss structures, which are respectively stuck in the card slots opened on the side walls at the inlet part of the inlet duct 1, forming a simply supported structure at the inlet part of the inlet duct 1 to make the configuration stable.

[0075] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the jet support plate 2 is a split structure and is connected by welding.

[0076] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the anti-icing cavity and its anti-icing air holes are located at the leading edge part of the jet support plate 2;

[0077] The anti-icing air holes are inclined towards the trailing edge direction of the jet support plate 2, so that the anti-icing air flowing out from it can flow from front to back, effectively covering the surface of the jet support plate 2 and effectively preventing icing.

[0078] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the open end of the jet support plate 2 has a positioning groove;

[0079] The outer wall of the end of the jet pipe 6 facing the cover plate 3 has a positioning protrusion, which is stuck in the positioning groove. During assembly, it is easy to achieve the positioning of the jet pipe 6 and the jet nozzle 7.

[0080] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the jet nozzle 7 is a centrifugal nozzle, which has a good atomization effect on the pre-cooling liquid and can improve the pre-cooling effect on the air flow at the inlet part of the inlet duct 1.

[0081] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the cross-section of the jet pipe 6 is approximately rectangular, or it can be other shapes, which is convenient for assembly;

[0082] The jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct further includes:

[0083] A jet nozzle mounting seat 10, which has opposite flanges, and is clamped on the opposite edges on both sides of the jet pipe 6 with opposite clamping edges, and has threaded holes communicating with the jet holes;

[0084] The jet nozzle 7 is screwed into the threaded hole.

[0085] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, it further includes:

[0086] A gasket 11, which is placed between the jet nozzle 7 and the jet nozzle mounting seat 10.

[0087] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, it further includes:

[0088] A spacer 12, which is placed between the jet support plate 2 and the jet nozzle 7.

[0089] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, there are multiple limiting grooves in the jet cavity;

[0090] There are multiple jet pipes 6 and their corresponding components and structures, and each jet pipe 6 is arranged in a corresponding limiting groove;

[0091] The specific number and distribution positions of the jet pipes 6 and their corresponding components and structures and the limiting grooves can be determined by those skilled in the art according to the specific actual situation when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0092] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, the jet nozzles 7 corresponding to each jet pipe 6 are distributed on both sides of the jet support plate 2. The specific distribution positions can be determined by those skilled in the art according to the specific actual situation when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0093] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the aerospace plane engine inlet duct, there are multiple jet nozzles 7 corresponding to each jet pipe 6 and their corresponding components and structures, and the jet nozzles 7 on each jet pipe 6 are distributed along the axial direction of the jet support plate 2;

[0094] The specific quantity and distribution positions of the jet nozzles 7 corresponding to each jet tube 6 and their corresponding components and structures can be determined by those skilled in the art according to the specific actual situation when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0095] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the air-breathing engine inlet of the spaceplane, there are multiple anti-icing air-intake holes axially distributed on both sides of the jet strut 2. The specific quantity and distribution positions thereof can be determined by those skilled in the art according to the specific actual situation when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0096] In some alternative embodiments, in the above jet pre-cooling structure at the inlet of the air-breathing engine inlet of the spaceplane, there are multiple jet struts 2 and their corresponding components and structures;

[0097] Each jet strut 2 is radially arranged and distributed at the inlet part of the air intake duct 1, or arranged and distributed according to a certain rule;

[0098] The specific quantity and distribution positions of the jet strut 2 can be determined by those skilled in the art according to the specific actual situation when applying the technical solution disclosed in this application, and no more detailed description will be given here.

[0099] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same and similar parts among the various embodiments, reference can be made to each other.

[0100] So far, the technical solution of this application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of this application is obviously not limited to these specific embodiments. Without departing from the principle of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this application.

Claims

1. An inlet jet pre-cooling structure for a spaceplane engine inlet, characterized in that, Comprising: An air inlet duct (1); A jet strut (2), in a leaf shape, supported at the inlet part of the air inlet duct (1), having a jet cavity and an anti-icing cavity inside, and having a jet orifice communicating with the jet cavity and an anti-icing air intake hole communicating with the anti-icing cavity on its side wall, one end of which exposes from the side wall of the air inlet duct (1), and this end having an opening communicating with the jet cavity and the anti-icing cavity; A cover plate (3), connected to the jet strut (2), sealing the opening, and having a pre-cooling liquid inflow hole communicating with the jet cavity and an anti-icing air inlet hole communicating with the anti-icing cavity thereon; A pre-cooling liquid nozzle (4), installed in the pre-cooling liquid inflow hole; An anti-icing air nozzle (5), installed in the anti-icing air inlet hole; A jet pipe (6), arranged in the jet cavity, one end of which is blocked, and the other end communicating with the pre-cooling liquid inflow hole, and having jet holes on its side wall; A jet nozzle (7), installed in the jet holes; A spacer block (8), arranged in the jet cavity, abutting against the jet pipe (6) to make the jet nozzle (7) leak out from the jet orifice; A heat-insulating and vibration-proof pad (9), filled in the jet cavity and covering the jet pipe (6); The anti-icing cavity and the anti-icing air intake hole are located at the leading edge part of the jet strut (2); The anti-icing air intake hole is inclined towards the trailing edge direction of the jet strut (2).

2. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 1, characterized in that, Both ends of the jet strut (2) have boss structures, respectively clamped in the clamping grooves opened on the side walls of the inlet part of the air inlet duct (1).

3. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 1, characterized in that, The jet strut (2) is of a split structure.

4. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 1, characterized in that, One end of the jet strut (2) with the opening has a positioning groove; The outer wall of one end of the jet pipe (6) facing the cover plate (3) has a positioning protrusion, which is clamped in the positioning groove.

5. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 1, characterized in that, The jet nozzle (7) is a centrifugal nozzle.

6. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 1, characterized in that, The cross-section of the jet pipe (6) is approximately rectangular; The jet pre-cooling structure at the inlet of the air-breathing engine of the spaceplane further comprises: A jet nozzle mounting seat (10), having opposite flanges thereon, and clamping on the opposite edges on both sides of the jet pipe (6) with the opposite clamping edges, and having threaded holes communicating with the jet holes thereon; The jet nozzle (7) is screwed into the threaded holes.

7. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 6, characterized in that, Also comprising: A gasket (11), padded between the jet nozzle (7) and the jet nozzle mounting seat (10).

8. The inlet jet pre-cooling structure for a spaceplane engine inlet according to claim 6, characterized in that, Also comprising: A spacer (12), padded between the jet strut (2) and the jet nozzle (7).

9. The inlet jet pre-cooling structure of the air-breathing hypersonic vehicle engine intake according to claim 1, characterized in that, There are a plurality of limiting grooves in the jet cavity; There are a plurality of the jet pipes (6) and their corresponding components and structures, and each jet pipe (6) is correspondingly arranged in one of the limiting grooves.

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