Pneumatic plug type spray pipe capable of being used for liquid rocket engine and manufacturing method of pneumatic plug type spray pipe

Abstract

The invention discloses a pneumatic plug type spray pipe capable of being used for a liquid rocket engine and a manufacturing method of the pneumatic plug type spray pipe, and belongs to the technical field of liquid rocket engines, heat engines and machine manufacturing. The engine is manufactured through 3D printing and comprises an inner ring spray pipe and an outer ring spray pipe, the inner ring spray pipe is provided with a double-layer cooling flow channel, and the outer ring spray pipe is provided with a single-layer cooling flow channel. The double-layer cooling flow channel not only can reduce the temperature of fluid in the first layer of flow channel, but also can cool the combustion chamber and the thrust chamber wall, and part of fluid is supplied into the thrust chamber for further cooling; the cooling scheme and the manufacturing mode are reasonably selected, different circulation modes are combined, the cooling problem of the pneumatic plug type spray pipe is solved, the development and proofing cost is reduced through the 3D printing advantage, and the engine performance and manufacturing convenience are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of liquid rocket engine manufacturing, in particular to a pneumatic plug nozzle for liquid rocket engine and a manufacturing method thereof. BACKGROUND

[0002] With the maturity of 3D printing technology, it is possible to manufacture rocket engines using metal 3D printing. However, existing 3D printing technology often requires support, increasing the complexity and cost of manufacturing. At the same time, although the pneumatic plug nozzle has good height compensation characteristics and is suitable for 3D printing, it has the problem of cooling difficulty. The cooling of the combustion chamber has always been a technical problem, and the design of the regenerative cooling channel of the inner ring combustion chamber wall also faces challenges.

[0003] To solve the above problems, the present application proposes a new type of liquid rocket engine, which aims to take advantage of the advantages of 3D printing technology, combine innovative cooling channel design, overcome the cooling defects of the pneumatic plug nozzle, reduce development costs, and improve engine performance. SUMMARY

[0004] The purpose of the present application is to provide a pneumatic plug nozzle for liquid rocket engine with good cooling effect, low manufacturing cost and superior performance.

[0005] To achieve the above purpose, the present application provides the following technical scheme: A pneumatic plug nozzle for liquid rocket engine, comprising a pneumatic plug nozzle manufactured by 3D printing, the pneumatic plug nozzle comprises an inner ring nozzle and an outer ring nozzle, the inner ring nozzle is provided with a double-layer cooling channel, and the outer ring nozzle is provided with a single-layer cooling channel; the inner ring nozzle and the outer ring nozzle are connected through an injector, and an additional connecting structure can be further arranged to strengthen the connection strength of the two.

[0006] Specifically, in the double-layer cooling channel, the second layer cooling channel not only reduces the temperature of the fluid in the first layer cooling channel, but also cools the wall of the combustion chamber and the thrust chamber; part of the fluid in the cooling channel can be supplied into the thrust chamber to further reduce the wall temperature.

[0007] Specifically, the injector used in the pneumatic plug nozzle is a gas-liquid coaxial injector.

[0008] Specifically, the outer ring nozzle is provided with only a single-layer cooling channel.

[0009] Specifically, the cooling scheme of the cooling channel includes two optional schemes: the first scheme is that the fluids in the two-layer cooling channel are both liquid fuel; the second scheme is that the fluid in the first layer cooling channel is fuel, and the fluid in the second layer cooling channel is liquid nitrogen.

[0010] Specifically, the fuel uses methane as fuel and oxygen as oxidant.

[0011] A manufacturing method of a pneumatic plug nozzle applicable to a liquid rocket engine, comprising: using 3D printing, specifically, printing a second layer of cooling flow channel and brazing it to the first layer of cooling flow channel; the flow channel can also be processed by pressure processing, and is welded to the outer wall of the inner ring nozzle one by one, and can also be welded to the outer wall of the first layer of cooling flow channel.

[0012] The beneficial effects of the present application are: The present application utilizes the shape characteristics of the pneumatic plug nozzle suitable for 3D printing, adopts 3D printing manufacturing, reduces the development and sample making cost, and is convenient for manufacturing integrated structure. By setting the double-layer cooling flow channel, the poor heating property of the pneumatic plug nozzle is effectively improved, the cooling of the plug nozzle combustion chamber is ensured, the design difficulty of the regenerative cooling flow channel of the inner ring combustion chamber wall is solved. And it can be flexibly selected according to actual needs, adapt to different cycle modes, improve the applicability and performance of the engine. The recommended fuel, oxidant and coolant combination, and the corresponding fluid supply mode, further optimize the cooling effect, and the safety is higher.

[0013] The above description is only a summary of the technical scheme of the present application, in order to more clearly understand the technical means of the present application, and can be implemented according to the content of the specification, the following will be described in detail with the preferred embodiments of the present application and the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0014] Fig. 1 It is a half cut structure side view of the pneumatic plug nozzle shown in the present application; Fig. 2 It is a half cut structure side view of the inner ring two-layer flow channel integration shown in the present application. DETAILED DESCRIPTION

[0015] The technical scheme of the present application will be described in detail below with reference to the drawings, obviously, the described embodiments are part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the present application.

[0016] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0017] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0018] In addition, the technical features involved in the different embodiments of the application described below can be combined with each other as long as they do not conflict with each other.

[0019] Reference Figs. 1-2 The present application provides a kind of aerodynamic plug nozzle that can be used in liquid rocket engine, mainly using 3D printing manufacturing method, aerodynamic plug nozzle includes inner ring nozzle 1 and outer ring nozzle 2, inner ring nozzle 1 is provided with double-layer cooling flow channel, outer ring nozzle 2 is provided with 1 layer cooling flow channel. Inner ring nozzle 1 and outer ring nozzle 2 are connected by injector 3.

[0020] The second layer cooling flow channel not only can reduce the temperature of the fluid in the first layer cooling flow channel, but also can be used to cool the combustion chamber and the thrust chamber wall, ensuring the cooling of the plug nozzle combustion chamber which is difficult to cool in the past, so that the regenerative cooling flow channel design of the inner ring combustion chamber wall is no longer difficult. Part of the fluid in the cooling flow channel is supplied into the thrust chamber to further reduce the wall temperature.

[0021] Cooling scheme selection Two kinds of cooling schemes can be selected, the first kind is that both two-layer cooling flow channels are connected with liquid fuel; the second kind is that the fluid in the first layer cooling flow channel is fuel, and the fluid in the second layer cooling flow channel is liquid nitrogen. Methane is recommended to be used as fuel, oxygen is recommended to be used as oxidant, and liquid nitrogen is recommended to be used as the cooling agent of the second layer cooling flow channel. Liquid nitrogen can effectively reduce the wall temperature and will not react with the oxidant and fuel. When liquid nitrogen is supplied into the second layer cooling flow channel, it needs to be sent into the injection port close to the wall surface of the combustion chamber, or the liquid nitrogen can be allowed to enter the combustion chamber by punching holes on the thrust chamber wall.

[0022] Manufacturing method The 3D printing is used to print the aerodynamic plug nozzle, and the development and sample costs are reduced. For the double-layer cooling flow channel of the inner ring nozzle 1, if the 3D printing of the second layer cooling flow channel is not convenient, the integrated manufacturing and welding of the cooling flow channel can be used, in particular, the second layer cooling flow channel can be printed and then brazed to the first layer; if the wall surface is smooth, the flow channel processed by pressure processing can be used, and the flow channel is welded to the outer wall of the inner ring or the outer wall of the first layer cooling flow channel. Brazing is suitable for the cooling flow channel wall printed integrally, and laser welding or automatic welding is suitable for the cooling flow channel wall manufactured separately. Heat treatment can improve the thermodynamic performance of the engine.

[0023] In addition, the 3D printed liquid collecting cavity usually has support, so it is recommended that the liquid collecting cavity and other structures are manufactured separately. If the mechanical properties of the 3D printed cooling flow channel or nozzle, combustion chamber or throat do not meet the requirements, mechanical manufacturing can still be used to achieve the desired effect. The inner ring and the connected structure, the outer ring and the connected structure can also be integrally printed, and then welded with the injector to manufacture, or the outer ring and the inner ring can be integrally machined and then welded with the injector to obtain a more optimized manufacturing scheme and performance.

[0024] Cycle mode adaptation For the supplementary combustion cycle mode, the fluid of the first layer and the outer ring cooling flow channel is used to supply the supplementary combustion cycle combustion chamber to ensure the temperature in the supplementary combustion cycle combustion chamber. For the expansion cycle mode, the fluid of the first layer and the outer ring cooling flow channel is still used to ensure the inlet temperature of the expansion cycle turbine. For the expansion cycle system, an optional scheme is to simply deliver the same regenerative cooling flow channel fluid to the expansion cycle turbine.

[0025] The technical features of the above-mentioned embodiments can be combined in any way. In order to make the description simple, all possible combinations of the technical features in the above-mentioned embodiments are not described, but as long as the combinations of the technical features do not exist, they should be considered as the scope of the description.

[0026] The above-mentioned embodiments only express several embodiments of the present application, and the description is more specific and detailed, but it should not be understood as a limitation on the scope of the patent. It should be pointed out that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of the present application. Therefore, the protection scope of the patent of the present application should be subject to the appended claims.

Claims

1. A pneumatic plug nozzle for use in liquid rocket engines, characterized in that, The invention includes a pneumatic plug nozzle manufactured using 3D printing. The pneumatic plug nozzle comprises an inner ring nozzle and an outer ring nozzle. The inner ring nozzle is provided with a double-layer cooling channel, and the outer ring nozzle is provided with a single-layer cooling channel. The inner ring nozzle and the outer ring nozzle are connected by an injector, and additional connection structures can be provided to strengthen the connection between the two.

2. A pneumatic plug nozzle for use in a liquid rocket engine according to claim 1, characterized in that, In the dual-layer cooling channel, the second cooling channel is not only used to reduce the temperature of the fluid in the first cooling channel, but also to cool the walls of the combustion chamber and thrust chamber; some of the fluid in the cooling channel can be supplied to the thrust chamber to further reduce the wall temperature.

3. A pneumatic plug nozzle for use in a liquid rocket engine according to claim 1, characterized in that, The outer ring nozzle is equipped with only a single-layer cooling channel.

4. A pneumatic plug nozzle for use in a liquid rocket engine according to claim 2, characterized in that, The cooling scheme of the cooling channel includes two options: the first is that the fluid in both cooling channels is liquid fuel; the second is that the fluid in the first cooling channel is fuel and the fluid in the second cooling channel is liquid nitrogen.

5. A pneumatic plug nozzle for use in a liquid rocket engine according to claim 4, characterized in that, The fuel uses methane as fuel and oxygen as an oxidant.

6. A method for manufacturing a pneumatic plug nozzle for a liquid rocket engine according to claim 1, characterized in that, include: Using 3D printing, the entire second layer of cooling channels can be printed and then brazed onto the first layer of cooling channels; alternatively, channels can be pressure-processed and then welded one by one to the outer wall of the inner ring nozzle, or to the outer wall of the first layer of cooling channels.

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