A hypersonic ramjet engine wall liquid metal and fuel inside and outside composite double-layer cooling channel structure and hypersonic ramjet engine

Abstract

The present application relates to the technical field of hypersonic scramjet heat protection, and particularly relates to a hypersonic scramjet wall liquid metal and fuel inner-outer composite double-layer cooling channel structure and a hypersonic scramjet. The hypersonic scramjet wall liquid metal and fuel inner-outer composite double-layer cooling channel structure comprises: a body; a first cooling structure and a second cooling structure, the first cooling structure and the second cooling structure are arranged in the body, and the first cooling structure and the second cooling structure are arranged in a stacked manner, the first cooling structure is provided with a first cooling medium, and the second cooling structure is provided with a second cooling medium; the strong heat exchange capacity of the first cooling medium is used to quickly and efficiently transfer the heat transferred by the combustion gas to the second cooling medium, the flow of the first cooling medium is changed by a first pump body, the temperature distribution of the combustion chamber wall can be actively controlled, and the heat dissipation intensity of the combustion gas to the wall can be adjusted.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of hypersonic scramjet thermal protection, in particular to a hypersonic scramjet wall liquid metal and fuel internal and external composite double-layer cooling channel structure and hypersonic scramjet. BACKGROUND

[0002] The full name of the hypersonic scramjet is supersonic combustion ramjet, which refers to a ramjet that burns fuel in a supersonic airflow. It can obtain oxygen from the atmosphere during flight. Fuel is sprayed from the wall or strut, mixed with high-speed airflow in the supersonic combustion chamber, and finally burned. The burned gas is ejected through the expansion nozzle to generate thrust.

[0003] Because of the supersonic combustion in its combustion chamber, the thermal environment is extremely harsh, and thermal protection means must be used to ensure that the engine wall works normally and is not burned out. The thermal protection technology of hypersonic scramjet can be roughly divided into three types according to the principle: passive, semi-passive and active.

[0004] Among them, the active type refers to using low-temperature or normal-temperature cooling medium for protection, and all or most of the heat is taken away by the working medium. When using fuel as a wall cooling medium for a hydrocarbon fuel hypersonic scramjet, there is a problem of fuel coking and blocking the wall cooling channel under high temperature conditions. Cooling channel blockage will lead to thermal protection failure, and in such a harsh thermal environment, it will cause the wall to burn out. In addition, under the "robust hypersonic scramjet" plan, the amount of fuel required for cooling exceeds the amount of fuel required for combustion, which means that the aircraft needs to carry additional fuel, which will reduce the effective payload of the aircraft. SUMMARY

[0005] Therefore, the technical problem to be solved by the present application is to overcome the problem of fuel coking and blocking the wall cooling channel under high temperature conditions when using fuel as a wall cooling medium for a hypersonic scramjet in the prior art, thereby providing a hypersonic scramjet wall liquid metal and fuel internal and external composite double-layer cooling channel structure and hypersonic scramjet.

[0006] In order to solve the above technical problems, the present application provides a hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure, comprising: a body; a first cooling structure and a second cooling structure, the first cooling structure and the second cooling structure are arranged in the body, and the first cooling structure and the second cooling structure are arranged in a stacked manner, the first cooling structure is provided with a first cooling medium, and the second cooling structure is provided with a second cooling medium; a first pump body arranged at one end of the first cooling structure, the first pump body is used for driving the first cooling medium to flow in the first cooling structure; a second pump body arranged at one end of the second cooling structure, the second pump body is used for driving the second cooling medium to flow in the second cooling structure; and a heat insulation layer arranged on one side of the body.

[0007] Further, the first cooling structure and the second cooling structure comprise a plurality of cooling channels, and the plurality of cooling channels are arranged in a spaced manner.

[0008] Further, the cooling channels of the first cooling structure and the cooling channels of the second cooling structure are arranged in a one-to-one correspondence.

[0009] Further, the cooling channels of the first cooling structure and the cooling channels of the second cooling structure are arranged in a staggered manner.

[0010] Further, the cross section of the cooling channel is rectangular.

[0011] Further, the cross section of the cooling channel is circular.

[0012] Further, the first cooling medium is liquid metal, and the second cooling medium is aviation kerosene.

[0013] Further, the liquid metal is made of gallium-indium alloy or sodium-potassium alloy.

[0014] Further, the first pump body is an electromagnetic pump, and the second pump body is a fuel pump.

[0015] The present application also provides a hypersonic scramjet engine comprising the hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure.

[0016] The technical scheme of the present application has the following advantages:

[0017] 1. The hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure provided by the present application comprises a body, a first cooling structure and a second cooling structure arranged in the body, the first cooling structure and the second cooling structure are arranged in a stacked manner, the first cooling structure is provided with a first cooling medium, and the second cooling structure is provided with a second cooling medium; a first pump body arranged at one end of the first cooling structure and used for driving the first cooling medium to flow in the first cooling structure; a second pump body arranged at one end of the second cooling structure and used for driving the second cooling medium to flow in the second cooling structure; and a heat insulation layer arranged on one side of the body.

[0018] By arranging the first cooling structure and the second cooling structure in the body and arranging the first cooling structure and the second cooling structure in a stacked manner, the first cooling medium of the first cooling structure can transfer heat to the second cooling medium of the second cooling structure after absorbing heat transferred to the combustion chamber wall by the fuel gas, and the second cooling medium can absorb the heat transferred by the second cooling medium to complete the preheating process of the fuel. The strong heat exchange capacity of the first cooling medium can realize effective heat protection of the engine wall surface, and in addition, the heat transfer of the first cooling medium in the first cooling structure to the second cooling medium in the second cooling structure is similar to heat exchange in a heat exchanger, so that the fuel can be heated to a higher temperature, thereby improving the heat sink of the fuel and reducing the amount of the cooling medium used.

[0019] The hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure can quickly and efficiently transfer the heat transferred by the fuel gas to the second cooling medium by using the strong heat exchange capacity of the first cooling medium, can actively control the temperature distribution of the combustion chamber wall surface and adjust the heat dissipation intensity of the fuel gas to the wall surface by changing the flow of the first cooling medium through the first pump body. Meanwhile, the channel cross-sectional size is increased, the possibility of coking and carbon deposition blocking the channel is reduced, the fuel can be heated to a higher temperature, the heat sink of the fuel is improved, the amount of the cooling medium used is reduced, and the problem of engine wall surface burning caused by high-temperature coking and blocking of the cooling channel by using only fuel as the regenerative cooling working medium is solved.

[0020] 2. The hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure provided by the present application, the cooling channels of the first cooling structure and the cooling channels of the second cooling structure are arranged one by one, which facilitates the direct heat exchange between the first cooling medium in the cooling channel of the first cooling structure and the second cooling medium in the cooling channel of the second cooling structure, and avoids the occurrence of energy loss.

[0021] 3. The hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure provided by the present application, the cooling channels of the first cooling structure can also be staggered with the cooling channels of the second cooling structure, which can better increase the support strength of the body and avoid the deformation of the body.

[0022] The summary is provided to introduce a selection of concepts in a simplified form, which will be further described below in the detailed description. The summary is not intended to identify key or essential features of the disclosure, nor is it intended to limit the scope of the disclosure. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings required to be used in the specific embodiments or prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0024] Figure 1 The structure diagram of the hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure provided by the present application;

[0025] Figure 2 The Figure 1 cross-sectional view.

[0026] Explanation of reference signs:

[0027] 1, body; 2, first cooling structure; 3, second cooling structure; 4, heat insulation layer; 5, cooling channel; 6, first cooling medium; 7, second cooling medium; 8, first pump body; 9, second pump body. DETAILED DESCRIPTION

[0028] In the following, only some exemplary embodiments are simply described. As those skilled in the art can recognize, the described embodiments can be modified in various different ways without departing from the spirit or scope of the present disclosure. Therefore, the drawings and the description are considered to be essentially exemplary rather than limiting.

[0029] In the description of the disclosure, it needs to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "straight", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" 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 disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the disclosure. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the disclosure, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0030] In the description of the disclosure, it needs to be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection or can communicate with each other; it can be directly connected, or indirectly connected through intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the disclosure can be understood according to the specific circumstances.

[0031] In the disclosure, unless otherwise explicitly specified and limited, the first feature "on" or "under" the second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the first feature "on", "above" and "on" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "under", "below" and "under" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0032] The disclosure below provides many different embodiments or examples for implementing different structures of the disclosure. For the sake of simplicity, the description below of a particular embodiment or example does not necessarily include all features that are equivalent to those from other embodiments or examples of the disclosure. Of course, this is merely an example, and the purpose is not to limit the disclosure. Moreover, the disclosure can refer to a reference numeral and / or a reference letter repeatedly in different examples, and such repetition is for the sake of simplicity and clarity and does not itself indicate a relationship between the various embodiments and / or examples discussed. Furthermore, the disclosure provides examples of various specific processes and materials, but one of ordinary skill in the art can realize that other processes can be applied and / or other materials can be used.

[0033] The preferred embodiments of the disclosure are described below in conjunction with the accompanying drawings, which should be understood as merely illustrative and explanatory, and not restrictive of the disclosure.

[0034] Referring to Figures 1 to 2 As shown in the drawings, the present application provides a hypersonic scramjet engine wall liquid metal and fuel internal and external composite double-layer cooling channel structure, comprising: a body 1; a first cooling structure 2 and a second cooling structure 3, the first cooling structure 2 and the second cooling structure 3 are arranged in the body 1, and the first cooling structure 2 and the second cooling structure 3 are arranged in a stacked manner, the first cooling structure 2 is provided with a first cooling medium 6, and the second cooling structure 3 is provided with a second cooling medium 7; a first pump body 8 arranged at one end of the first cooling structure 2, the first pump body 8 is used to drive the first cooling medium 6 to flow in the first cooling structure 2; a second pump body 9 arranged at one end of the second cooling structure 3, the second pump body 9 is used to drive the second cooling medium 7 to flow in the second cooling structure 3; a heat insulation layer 4 arranged on one side of the body 1.

[0035] By arranging the first cooling structure 2 and the second cooling structure 3 in the body 1, and arranging the first cooling structure 2 and the second cooling structure 3 in a stacked manner, the first cooling medium 6 of the first cooling structure 2 transmits heat to the second cooling medium 7 of the second cooling structure 3 after absorbing heat from the combustion chamber wall, and the second cooling medium 7 absorbs the heat transmitted by the second cooling medium 7, completing the preheating process of the fuel. The strong heat exchange capacity of the first cooling medium 6 can realize effective heat protection of the engine wall, and in addition, the heat transfer of the first cooling medium 6 in the first cooling structure 2 to the second cooling medium 7 in the second cooling structure 3 is similar to the heat exchange of a heat exchanger, which can heat the fuel to a higher temperature, thereby improving the fuel heat sink and reducing the amount of cooling medium used.

[0036] The wall liquid metal of the scramjet engine and the fuel inner and outer composite double cooling channel structure utilizes the strong heat exchange capacity of the first cooling medium 6 to quickly and efficiently transfer the heat transferred by the gas and transfer it to the second cooling medium 7. By changing the flow of the first cooling medium 6 through the first pump body 8, the temperature distribution of the combustion chamber wall can be actively controlled, and the heat dissipation intensity of the gas to the wall can be adjusted. At the same time, increasing the cross-sectional size of the channel reduces the possibility of coking and carbon deposition blocking the channel, realizes heating the fuel to a higher temperature, improves the heat sink of the fuel, reduces the use amount of the cooling medium, and solves the problem of engine wall burning caused by high-temperature coking and blocking of the cooling channel 5 using only fuel as the regenerative cooling working medium.

[0037] wherein, Figure 2 In the first cooling structure 2, the bottom is the gas side, and the generated combustion heat in the combustion chamber is transferred through the first cooling structure 2 and the second cooling structure 3.

[0038] The heat insulation layer 4 has the characteristics of high temperature resistance and low thermal conductivity. The arrangement of the heat insulation layer 4 effectively reduces the influence of heat transfer on other components.

[0039] In this embodiment, the first cooling medium 6 is a liquid metal, and the second cooling medium 7 is aviation kerosene. The heat exchange process of the liquid metal is a physical process, so there is no chemical reaction to block the wall first cooling structure 2 and the second cooling structure 3.

[0040] In some optional embodiments, the first cooling structure 2 and the second cooling structure 3 include a plurality of cooling channels 5, and the plurality of cooling channels 5 are arranged at intervals. Among them, the cooling channel 5 is a microchannel, that is, the size of the cooling channel 5 is small, which is a nanoscale channel.

[0041] In order to facilitate the processing of the plurality of cooling channels 5 in the body 1, therefore, the cross section of the cooling channel 5 is made into a rectangle.

[0042] Of course, the cross section of the cooling channel 5 can also be made into a circle or a square, a triangle. Specifically, it can be set according to actual needs.

[0043] In some optional embodiments, the cooling channel 5 of the first cooling structure 2 and the cooling channel 5 of the second cooling structure 3 are arranged one by one. This arrangement facilitates the direct heat exchange between the first cooling medium 6 in the cooling channel 5 of the first cooling structure 2 and the second cooling medium 7 in the cooling channel 5 of the second cooling structure 3, avoiding energy loss.

[0044] Of course, the cooling channel 5 of the first cooling structure 2 can also be staggered with the cooling channel 5 of the second cooling structure 3. This arrangement can better increase the support strength of the body 1 and avoid deformation of the body 1.

[0045] In the embodiment, the liquid metal is made of gallium-indium alloy or sodium-potassium alloy.

[0046] The body 1 is made of high-temperature alloy. Specifically, it can be stainless steel 316L.

[0047] The first pump body 8 is an electromagnetic pump, and the second pump body 9 is a fuel pump.

[0048] The liquid metal and fuel inner-outer composite double-layer cooling channel structure of the scramjet engine wall surface quickly and efficiently transfers the heat transferred by the combustion gas to the second cooling medium 7 by using the strong heat exchange capacity of the first cooling medium 6, and the temperature distribution of the combustion chamber wall surface can be actively controlled by changing the flow of the first cooling medium 6 through the first pump body 8, and the heat dissipation intensity of the combustion gas to the wall surface can be adjusted. At the same time, increasing the cross-sectional size of the channel can reduce the possibility of coking and carbon deposition blocking the channel, realize heating the fuel to a higher temperature, improve the heat sink of the fuel, reduce the use amount of the cooling medium, solve the problem of engine wall surface burning caused by high-temperature coking and blocking of the cooling channel 5 using only fuel as the regenerative cooling working medium.

[0049] The application further provides a scramjet engine comprising the liquid metal and fuel inner-outer composite double-layer cooling channel structure of the scramjet engine wall surface.

[0050] Obviously, the above embodiments are only examples for clearly illustrating, but not limitation to the embodiments. For those skilled in the art, other different forms of changes or variations can be made on the basis of the above description. Here, all the embodiments need not and cannot be exhausted. The obvious changes or variations derived therefrom are still within the protection scope of the application.

Claims

1. A hypersonic scramjet engine wall liquid metal and fuel inner-outer composite double-layer cooling channel structure, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

2. The hyper- scramjet engine wall liquid metal and fuel inner-outer composite double-layer cooling passage structure according to claim 1, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

3. The hyper- scramjet engine wall liquid metal and fuel inner-outer composite double-layer cooling passage structure according to claim 2, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

4. The hyper- scramjet engine wall liquid metal and fuel inner-outer composite double-layer cooling passage structure according to claim 2, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

5. The liquid metal and fuel inside-out combined double-layer cooling channel structure of a scramjet wall surface according to any one of claims 2-4, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

6. The hybrid hypersonic scramjet wall liquid metal and fuel inner-outer composite double-layer cooling channel structure according to claim 5, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

7. The hyper- scramjet engine wall liquid metal and fuel inner-outer composite double-layer cooling passage structure according to claim 1, characterized in that, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface.

8. A scramjet engine characterized by, The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling channel structure of a hypersonic scramjet engine wall surface. The application relates to a liquid metal and fuel inner-outer composite double-layer cooling

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