Injector and thrust chamber

Abstract

The invention provides an injector and a thrust chamber. The injector is arranged at the head of a thrust chamber of the liquid rocket engine and connected with a top cover component of the head, a second propellant inlet is formed in the top cover component, the injector comprises a hollow cylinder part, a first propellant inlet is formed in the top of the cylinder part, and multiple layers of nozzles arranged at intervals in the axial direction of the cylinder part are formed in the nozzle section, close to the bottom end, of the cylinder part. The multiple nozzles in each layer are arranged in the circumferential direction of the barrel part, and the axes of the nozzles intersect with the outer circumferential wall of the barrel part and are not perpendicular to the outer circumferential wall of the barrel part. The first propellant is sprayed out in the direction surrounding the circumferential direction of the barrel part, the first propellant is sprayed out in the vortex shape in the first plane perpendicular to the barrel part, the momentum of the first thrust agent reaching the front end of the cooling liquid film is reduced, the movement stroke of the first propellant on the projection in the radial direction of the barrel part is shortened, and the cooling efficiency is improved. Therefore, the first propellant is prevented from puncturing the cooling liquid film, the condition that the cooling liquid hole can be formed in the thrust chamber head is achieved, and the integrity of body production is guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of injectors, and in particular, to an injector and a thrust chamber. Background Art

[0002] The thrust chamber of a rocket engine is an important component that provides thrust to the rocket. The thrust chamber is generally composed of two parts: the head and the body. The most important part of the head is called the injector, which is a device for atomizing and mixing the engine propellant.

[0003] Pintle injectors are one of the most popular injectors due to their high combustion stability and strong adaptability to working conditions. In related technologies, the momentum of the oxidant ejected from the pintle head is often large, which will break through the cooling film formed by the liquid fuel and impact the inner wall of the thrust chamber, easily causing the liquid film cooling device extending from the head to fail.

[0004] Therefore, related technologies often require the introduction of body liquid film cooling, and a cooling liquid film inlet is opened in the body of the thrust chamber. This will cause the body structure of the thrust chamber and the integrity of production to be destroyed, introduce too much uncertainty into production, and thus increase the difficulty of producing the thrust chamber. Summary of the invention

[0005] In view of the shortcomings of the existing methods, the present application proposes an injector and a thrust chamber to solve the technical problem that the coolant film inlet is transferred to the thrust chamber body in the related technology, thereby destroying the integrity of the thrust chamber body design and production, introducing too much uncertainty into the production, and increasing the difficulty of thrust chamber production.

[0006] In the first aspect, an embodiment of the present application provides an injector, which is arranged at the head of the thrust chamber of a liquid rocket engine and connected to the top cover component of the head, the top cover component is provided with a second propellant inlet, includes a hollow barrel, the top of the barrel is provided with a first propellant inlet, and a nozzle section near the bottom end of the barrel is provided with multiple layers of nozzles arranged along the axial spacing thereof, and the multiple nozzles in each layer are arranged around the circumference of the barrel, and the axis of the nozzle intersects with the outer peripheral wall of the barrel and is not perpendicular.

[0007] Optionally, the axes of the orthographic projections of at least two layers of the nozzles in a first plane perpendicular to the barrel intersect or form an angle of 180 degrees, so as to cause the first propellant to be ejected in at least two directions.

[0008] Optionally, in any two adjacent layers of the nozzles, the position of the nozzles in one layer on the circumference of the barrel is different from the position of the nozzles in the other layer on the circumference of the barrel.

[0009] Optionally, the nozzle is a tangential hole opened on the side wall of the barrel, and the axis of the tangential hole forms an acute angle with the outer peripheral wall of the barrel.

[0010] Optionally, the axis of the nozzles of each layer is parallel to the first plane; Alternatively, the axis of the nozzle of each layer forms an angle with the first plane and is not perpendicular, so that the first propellant is sprayed obliquely toward the top end of the barrel or toward the bottom end of the barrel.

[0011] Optionally, the axis of at least one layer of the nozzles is inclined toward the bottom end of the barrel.

[0012] Optionally, the injector includes at least one of the following: Along the direction from the top end to the bottom end of the barrel, the aperture of each layer of the nozzle gradually increases; The number of the nozzles in each layer gradually increases along the direction from the top end to the bottom end of the barrel.

[0013] Optionally, the injector further comprises a connecting portion disposed around the outer peripheral wall of the barrel, wherein the connecting portion is used to be connected to the top cover component of the head.

[0014] In a second aspect, an embodiment of the present application provides a thrust chamber, comprising a head, wherein the head comprises a top cover member and an injector according to the above embodiment; The top cover member is annular and is arranged around the outer circumference of the injector. The top cover member has a cavity suitable for circulating the second propellant inside. The bottom surface of the top cover member is provided with an injection annular seam and a cooling annular hole connected to the cavity. The injection annular seam is close to the injector, and the cooling annular hole is located at an end away from the injector, and is used to form a cooling liquid film at a position close to the inner wall of the thrust chamber.

[0015] Optionally, the second propellant inlet is provided on an end surface of the top cover component away from the injector, and the second propellant inlet is communicated with the cavity.

[0016] The beneficial technical effects brought by the technical solution provided by the embodiment of the present application include: the present application designs a multi-layer nozzle at the bottom end of the barrel, and each layer of nozzles is provided with multiple nozzles around the circumference of the barrel, and the first propellant is dispersed to multiple nozzles of multiple layers, which can reduce the flow rate and momentum of the first propellant when it is sprayed from a single nozzle. Each nozzle can make the first propellant spray in a direction around the circumference of the barrel, extending the path of the first propellant to reach the cooling liquid film or the inner wall of the head of the thrust chamber. The first propellant sprayed in sections by multiple nozzles in the same layer is sprayed in a vortex state on the first plane (such as a radial plane) perpendicular to the barrel, and atomizing as much as possible before reaching the cooling liquid film can further reduce the momentum and dispersed flow rate of the first propellant when it reaches the cooling liquid film, so as to avoid the first propellant from penetrating the cooling liquid film as much as possible. This makes the present application have the conditions for setting the coolant hole on the head of the thrust chamber, so that there is no need to set the coolant hole in the body of the thrust chamber in order to avoid the first propellant from penetrating the cooling liquid film, which can ensure the integrity of the body production, thereby reducing the difficulty of body production.

[0017] The first propellant is sprayed in a vortex state so that it can be fully atomized before being mixed with the second propellant, thereby improving the atomization and mixing effect of the thrust chamber and allowing the fuel of the engine to be fully burned.

[0018] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic cross-sectional structure diagram of a head of a thrust chamber provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of an injector provided in an embodiment of the present application; Figure 3 A schematic cross-sectional structure diagram of an injector provided in an embodiment of the present application; Figure 4 A schematic diagram of the cross-sectional structure of a barrel portion of an injector provided in an embodiment of the present application on a first plane; Figure 5 A schematic diagram of the cross-sectional structure of a thrust chamber provided in an embodiment of the present application.

[0020] Description of reference numerals: 001-head; 002-body; 100-injector; 110- barrel; 111- first propellant inlet; 112- nozzle; 120-connecting part; 200 - top cover member; 210 - cavity; 220 - injection annular gap; 230 - cooling annular hole; 240 - second propellant inlet. DETAILED DESCRIPTION

[0021] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0022] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0023] In the related art, the oxidant in the pintle nozzle is mostly sprayed vertically toward the inner wall of the thrust chamber along the radial direct current hole, forming a vertical mutual impact atomization and mixing form with the axially ejected liquid fuel. Since the mixing ratio of the thrust chamber of the liquid rocket engine is mostly 2.0-3.0, the flow rate of the oxidant in the two propellants is much greater than the flow rate of the other combustible fuel. Therefore, the momentum of the oxidant ejected from the pintle head is often large, which will break through the cooling liquid film formed by the liquid fuel and impact the inner wall of the thrust chamber, causing the liquid film cooling device extending from the head to fail.

[0024] Therefore, in order to maintain the cooling effect on the body of the thrust chamber, related technologies often introduce body liquid film cooling, and transfer the cooling liquid film inlet to the body of the thrust chamber. This will lead to the destruction of the integrity of the design and production of the body of the thrust chamber, introduce too much uncertainty into the production, and thus increase the difficulty of producing the thrust chamber.

[0025] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0026] Reference Figure 1-Figure 5 The embodiment of the present application provides an injector 100. The injector 100 is disposed in the head 001 of the thrust chamber of the liquid rocket engine and connected to the top cover member 200 of the head 001. The top cover member 200 is provided with a second propellant inlet 240.

[0027] Reference Figure 2The injector 100 includes a hollow barrel 110, a first propellant inlet 111 is provided at the top of the barrel 110, a nozzle 112 section near the bottom end of the barrel 110 is provided with multiple layers of nozzles 112 arranged along the axial spacing thereof, and the multiple nozzles 112 of each layer are arranged around the circumference of the barrel 110, and the axis of the nozzle 112 intersects with the outer peripheral wall of the barrel 110 and is not perpendicular.

[0028] The present application designs a multi-layer nozzle 112 at the bottom end of the barrel 110, and each layer of nozzles 112 is provided with multiple nozzles 112 around the circumference of the barrel 110. The first propellant is dispersed to multiple nozzles 112 in multiple layers, which can reduce the flow rate and momentum of the first propellant when it is ejected from a single nozzle 112. Each nozzle 112 can make the first propellant ejected in a direction around the circumference of the barrel 110, extending the path of the first propellant to reach the cooling liquid film or the inner peripheral wall of the head of the thrust chamber; the first propellant discretely ejected by multiple nozzles in the same layer is ejected in a vortex state on a first plane (such as a radial plane) perpendicular to the barrel 110, and atomizing as much as possible before reaching the cooling liquid film can further reduce the momentum of the first propellant when it reaches the cooling liquid film and disperse the flow rate, thereby avoiding the first propellant from penetrating the cooling liquid film as much as possible. Therefore, there is no need to add cooling liquid holes in the body 002 of the thrust chamber because the first propellant may penetrate the cooling liquid film, so that the injector using the present application only needs to set the cooling liquid holes at the head 001 of the thrust chamber, which can ensure the integrity of the body 002 structure and reduce the difficulty of producing the body 002.

[0029] The first propellant is sprayed in a vortex state so that it can be fully atomized before being mixed with the second propellant, thereby improving the atomization and mixing effect of the thrust chamber and allowing the fuel of the engine to be fully burned.

[0030] Optionally, refer to Figure 3-Figure 5 At least two layers of nozzles 112 have axes of orthographic projection in a first plane perpendicular to the barrel 110 that intersect or form an angle of 180 degrees, so as to eject the first propellant in at least two directions.

[0031] When the first propellant is sprayed out in a swirling flow in at least two directions, the first propellant can be diffused more evenly, thereby improving the atomization and mixing effect of the first propellant and the second propellant.

[0032] In actual production, the directions of the first propellant sprayed from each layer of nozzles 112 may be different according to the number of layers of nozzles 112. Alternatively, the first propellant is sprayed in two directions, and the directions of the first propellant sprayed from two adjacent layers of nozzles 112 are different. Alternatively, the directions of the first propellant sprayed from any two layers of nozzles 112 are different.

[0033] Optionally, refer to Figure 3In order to make the first propellant diffuse more evenly around the annular surface of the outer wall of the barrel 110 while facilitating processing, the present application takes the example of the first propellant being sprayed in two directions and the axes of the orthographic projections of two adjacent layers of nozzles 112 in the first plane forming an angle of 180 degrees.

[0034] Optionally, in any two adjacent layers of nozzles 112 , the position of one layer of nozzles 112 in the circumferential direction of the barrel 110 is different from the position of the other layer of nozzles 112 in the circumferential direction of the barrel 110 .

[0035] Any two adjacent layers of nozzles 112 are staggered so that the first propellant diffuses more evenly around the outer peripheral wall of the barrel 110, thereby improving the atomization effect of the first propellant and improving the atomization and mixing effect of the first propellant and the second propellant.

[0036] Optionally, refer to Figure 4 The nozzle 112 is a tangential hole opened on the side wall of the barrel 110 , and the axis of the tangential hole forms an acute angle with the outer peripheral wall of the barrel 110 .

[0037] Since the nozzle 112 of the present application is designed as a tangential hole whose axis is at an acute angle to the outer peripheral wall of the barrel 110, when the first propellant flows into the tangential hole, it will be affected by the flow diversion of the tangential hole, generating a force inclined to the radial direction of the barrel 110, thereby changing the flow direction of the first propellant, so that the first propellant is ejected in a circumferential swirl around the outer peripheral wall of the barrel 110, so that the first propellant in the same layer generates a vortex flowing circumferentially around the barrel 110 in the first plane. Since the momentum of the first propellant at each nozzle 112 is reduced, the momentum of the first propellant is reduced when it reaches the front end of the cooling liquid film. In addition, since the first propellant at each nozzle 112 is ejected in a swirl manner, under the premise of being consistent with the momentum ejected in the radial direction of the barrel 110 in the prior art, the first propellant ejected in a swirl manner in the present application has a reduced movement stroke on the projection along the radial direction of the barrel 110, so that the first propellant is diffused more evenly, and the atomization and mixing effect of the first propellant and the second propellant is improved.

[0038] Optionally, the axis of each layer of nozzles 112 is parallel to the first plane. Alternatively, the axis of each layer of nozzles 112 is at an angle to the first plane and is not perpendicular, so that the first propellant is sprayed obliquely toward the top end of the barrel 110 or toward the bottom end of the barrel 110 .

[0039] When the axis of each layer of nozzles 112 is parallel to the first plane, the swirl surface formed by the first propellant sprayed from the nozzles 112 in the same layer is also parallel to the first plane. When the first propellant is sprayed obliquely upward or obliquely downward, the swirl surface formed by the first propellant sprayed from the nozzles 112 in the same layer is umbrella-shaped and three-dimensional along the axis of the barrel 110, which can further extend the movement stroke of the first propellant to reach the front end of the cooling liquid film, thereby further reducing the momentum of the first propellant before reaching the cooling liquid film, and further reducing the probability of the first propellant piercing the cooling liquid film.

[0040] At the same time, the first propellant is sprayed obliquely upward or downward, which also prolongs the movement stroke of the first propellant before contact with the second propellant, thereby improving the atomization effect of the first propellant and the second propellant before mixing.

[0041] In an optional embodiment, the axis of at least one layer of nozzles 112 is inclined toward the bottom end of the barrel 110 .

[0042] Since the second propellant surrounds the outer wall of the barrel 110 and is sprayed downward along the axis of the barrel 110, the first propellant is sprayed downward at an angle, thereby postponing the time for mixing the first propellant and the second propellant, so that the first propellant can be fully atomized before being mixed with the second propellant, thereby improving the atomization mixing effect of the first propellant and the second propellant.

[0043] In another optional embodiment, the axis of at least one layer of nozzles 112 in the lower layer of nozzles 112 is inclined toward the top of the barrel 110, and the axis of at least one layer of nozzles 112 in the upper layer of nozzles 112 is inclined toward the bottom of the barrel 110. When the first propellant is sprayed, it will produce mutual impact collision, thereby further improving the atomization effect of the first propellant, and then improving the atomization mixing effect of the first propellant and the second propellant.

[0044] In another optional embodiment, the axis of at least one layer of nozzles 112 located in the middle is parallel to the first plane, the axis of at least one layer of nozzles 112 in the lower layer is inclined toward the top of the barrel 110, and the axis of at least one layer of nozzles 112 in the upper layer is inclined toward the bottom of the barrel 110, so that the first propellant sprayed downwardly by the upper layer nozzles 112 and the first propellant sprayed upwardly by the lower layer nozzles 112 both collide with the first propellant sprayed from the middle along the direction parallel to the first plane, thereby effectively improving the atomization effect of the first propellant.

[0045] Optionally, the size of each nozzle 112 may be the same. Alternatively, the aperture of each layer of nozzles 112 may gradually increase from the top to the bottom of the barrel 110, thereby improving the atomization and mixing effect of the first propellant and the second propellant.

[0046] Optionally, the number of nozzles 112 in each layer is the same, or the number of nozzles 112 in each layer gradually increases from the top to the bottom of the barrel 110, thereby improving the atomization and mixing effect of the first propellant and the second propellant.

[0047] Optionally, refer to Figure 2 and Figure 3 The injector 100 of the embodiment of the present application further includes a connecting portion 120 disposed around the outer peripheral wall of the barrel 110, the connecting portion 120 is located at the top of the barrel 110 and is parallel to the first plane, and is used to connect with the top cover member 200. The top cover member 200 is also disposed around the outer peripheral wall of the barrel 110, the connecting portion 120 is plate-shaped, the plate-shaped connecting portion 120 is placed on the top surface of the top cover member 200, and the top cover member 200 is connected or welded by fasteners such as bolts.

[0048] Optionally, a positioning groove matching the shape of the connecting portion 120 is formed on the top surface of the top cover member 200, so as to locate the connection position between the injector 100 of the embodiment of the present application and the top cover.

[0049] The present application also provides a thrust chamber. Figure 1 The thrust chamber includes a head portion 001 and a body portion 002 connected to the head portion 001 , and the head portion 001 includes a top cover member 200 and the injector 100 of the above embodiment.

[0050] The top cover member 200 is annular and arranged around the outer periphery of the injector 100, and is connected to the connecting portion 120 of the injector 100. A second propellant inlet 240 is provided on the top cover member 200, and a cavity 210 suitable for circulating the second propellant is provided inside the top cover member 200. An injection annular slit 220 and a cooling annular hole 230 communicating with the cavity 210 are provided on the bottom surface of the top cover member 200, the injection annular slit 220 is close to the injector 100, and the cooling annular hole 230 is located at an end away from the injector 100, and is used to form a cooling liquid film at a position close to the inner wall of the thrust chamber.

[0051] The second propellant enters the cavity 210 from the second propellant inlet 240 and is ejected from the injection annular gap 220 along the axis of the injector 100 toward the bottom of the injector 100. After the first propellant is ejected from the nozzle 112 in a swirling state, it is atomized and mixed with the second propellant.

[0052] In the present application, a cooling ring hole 230 is opened on the top cover member 200 , and a coolant inlet is also arranged on the top cover member 200 , so that the coolant can be sprayed downwardly from the cooling ring hole 230 along the axis of the injector 100 to form a cooling liquid film for protecting the inner wall of the body 002 .

[0053] Due to the structure of the barrel 110 designed in the present application, the momentum of the first propellant before reaching the cooling liquid film is reduced, so that the momentum of the first propellant is insufficient to penetrate the cooling liquid film, that is, the injection flow field generated by the atomization and mixing of the first propellant and the second propellant will not interfere with the extension of the cooling liquid film. Therefore, the present application abandons the body cooling solution and introduces head cooling, that is, the cooling ring hole 230 is designed on the top cover component 200, which ensures the integrity of the production of the thrust chamber body 002 and reduces the production difficulty and production cost of the body 002.

[0054] By introducing head cooling by opening a cooling ring hole 230 on the top cover member 200, there is no need to add additional components to the thrust chamber, which facilitates the processing and production of the thrust chamber and is beneficial to the volume optimization of the engine.

[0055] Optionally, refer to Figure 1 and Figure 5 The second propellant inlet 240 is disposed on the end surface of the top cover component 200 away from the injector 100 , and the second propellant inlet is communicated with the cavity 210 .

[0056] When the second propellant is passed into the cavity 210 from the second propellant inlet 240, the second propellant is sprayed out from the cooling annular hole 230 and the injection annular gap 220. The second propellant sprayed from the injection annular gap 220 is used to be atomized and mixed with the first propellant to generate an injection flow field. The second propellant sprayed from the cooling annular hole 230 also serves as a coolant, and forms a coolant film in the process of extending downward to protect the inner wall of the body 002. This further simplifies the structure of the thrust chamber head 001, facilitating the processing and production of the thrust chamber.

[0057] Optionally, the first propellant and the second propellant are in the form of a liquid-liquid mixture. The present application is described by taking the example of using liquid oxygen as the first propellant and using kerosene as the second propellant.

[0058] Reference Figure 5 The body 002 of the thrust chamber includes a sandwich structure consisting of an inner side wall and an outer side wall, and a flow channel is arranged in the sandwich structure for the regeneration cooling flow channel of the fuel. The production and processing technology of the body 002 can be an additive manufacturing process or a diffusion linking process. Since the present application does not require the use of body cooling, the body 002 can be integrally formed from top to bottom, so that there are no upper and lower connecting welds on the inner side wall, no breakpoints, and no breakpoints on the outer side wall, which ensures the integrity of the production of the body 002 and reduces the difficulty of the production of the body 002. The head 001 and the thrust chamber body 002 are connected by a flange or welding, and no specific restrictions are made here.

[0059] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: The present application designs a multi-layer nozzle 112 at the bottom end of the barrel 110, and each layer of nozzles 112 is provided with multiple nozzles 112 around the circumference of the barrel 110. The first propellant is dispersed to multiple nozzles 112 in multiple layers, which can reduce the flow rate and momentum of the first propellant when it is ejected from a single nozzle 112. Each nozzle 112 can make the first propellant ejected in a direction around the circumference of the barrel 110, extending the path of the first propellant to reach the cooling liquid film or the inner peripheral wall of the head of the thrust chamber; the first propellant discretely ejected by multiple nozzles in the same layer is ejected in a vortex state on a first plane (such as a radial plane) perpendicular to the barrel 110, and is atomized as much as possible before reaching the cooling liquid film, which can further reduce the momentum of the first propellant when it reaches the cooling liquid film and disperse the flow rate, thereby avoiding the first propellant from penetrating the cooling liquid film as much as possible. Therefore, there is no need to add cooling liquid holes in the body 002 of the thrust chamber because the first propellant may penetrate the cooling liquid film, so that the injector using the present application only needs to set the cooling liquid holes at the head 001 of the thrust chamber, which can ensure the integrity of the body 002 structure and reduce the difficulty of producing the body 002.

[0060] In the present application, a cooling ring hole 230 is opened on the top cover member 200, and a coolant inlet is also arranged on the top cover member 200, so that the coolant can be sprayed downwardly from the cooling ring hole 230 along the axis of the injector 100 to form a cooling liquid film for protecting the inner wall of the body 002. The embodiment of the present application abandons the body cooling scheme and introduces head cooling, that is, the cooling ring hole 230 is designed on the top cover member 200, thereby ensuring the integrity of the production of the thrust chamber body 002 and reducing the production difficulty and production cost of the body 002.

[0061] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0062] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0063] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0064] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0065] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. An injector, arranged at the head of a thrust chamber of a liquid rocket engine and connected to a top cover member of the head, wherein the top cover member is provided with a second propellant inlet, characterized in that: It comprises a hollow barrel, a first propellant inlet is provided at the top of the barrel, a nozzle section near the bottom end of the barrel is provided with multiple layers of nozzles arranged along the axial spacing, a plurality of nozzles in each layer are arranged around the circumference of the barrel, and the axis of the nozzle intersects with the outer peripheral wall of the barrel and is not perpendicular.

2. The injector according to claim 1, characterized in that The axes of the orthographic projections of at least two layers of the nozzles in a first plane perpendicular to the barrel intersect or form an angle of 180 degrees.

3. The injector according to claim 1, characterized in that Among any two adjacent layers of the nozzles, the position of the nozzles in one layer on the circumferential direction of the barrel portion is different from the position of the nozzles in the other layer on the circumferential direction of the barrel portion.

4. The injector according to claim 1, characterized in that The nozzle is a tangential hole opened on the side wall of the barrel, and the axis of the tangential hole forms an acute angle with the outer peripheral wall of the barrel.

5. The injector according to claim 2, characterized in that The axis of the nozzles in each layer is parallel to the first plane; Alternatively, the axis of the nozzles in each layer forms an angle with the first plane and is not perpendicular.

6. The injector according to claim 4, characterized in that The axis of at least one layer of the nozzles is inclined toward the bottom end of the barrel.

7. The injector according to claim 1, characterized in that Include at least one of the following: Along the direction from the top end to the bottom end of the barrel, the aperture of each layer of the nozzle gradually increases; The number of the nozzles in each layer gradually increases along the direction from the top end to the bottom end of the barrel.

8. The injector according to claim 1, characterized in that It also includes a connecting portion disposed around the outer peripheral wall of the barrel portion, and the connecting portion is used to be connected to the top cover component of the head portion.

9. A thrust chamber, characterized in that: comprising a head, the head comprising a top cover member and an injector according to any one of claims 1 to 8; The top cover member is annular and is arranged around the outer circumference of the injector. The top cover member has a cavity suitable for circulating the second propellant inside. The bottom surface of the top cover member is provided with an injection annular seam and a cooling annular hole connected to the cavity. The injection annular seam is close to the injector, and the cooling annular hole is located at an end away from the injector, and is used to form a cooling liquid film at a position close to the inner wall of the thrust chamber.

10. The thrust chamber according to claim 9, characterized in that The second propellant inlet is disposed on the end surface of the top cover component away from the injector, and the second propellant inlet is communicated with the cavity.

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