A dual-channel cooling system for a scramjet engine
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- HARBIN INST OF TECH
- Filing Date
- 2023-03-07
- Publication Date
- 2026-07-21
Smart Images
Figure CN116181491B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of scramjet engine technology, and more specifically to a dual-channel cooling system for scramjet engines. Background Technology
[0002] As flight Mach numbers increase, the thermal load on the cooling wall gradually exceeds the upper limit of the fuel's heat absorption capacity, making insufficient fuel heat absorption capacity the core limitation of wall cooling. To make fuller use of the fuel's heat absorption capacity, endothermic decomposition reactions are usually performed on the fuel to obtain additional chemical heat absorption capacity. However, the outer coolant begins to undergo thermal decomposition and coking at 482°C, while thermal oxidation deposition coking begins to appear at 260°C. The high-carbon coke-like substances formed by coking adsorb onto the channel surface, causing a decrease in heat transfer performance and potentially completely blocking the cooling channels, thereby causing engine performance failure. Summary of the Invention
[0003] Therefore, the technical problem to be solved by the present invention is to overcome the coking problem in the cooling channel of the wall of a high heat flux engine in the prior art, thereby providing a dual-channel cooling system for a scramjet engine.
[0004] To address the aforementioned technical problems, this invention provides a dual-channel cooling system for a scramjet engine, comprising: a fuel tank containing an outer layer of coolant, the fuel tank being connected to a fuel pump; a combustion chamber having an outer cooling channel and an inner cooling channel within its wall; and an inner cooling circuit including a heat exchanger and inner cooling pipes. The inner coolant in the inner cooling pipes undergoes primary cooling of the combustion chamber wall via the inner cooling channel, and heat exchange is performed on the inner coolant using the heat exchanger. The outer coolant in the fuel tank enters the outer cooling channel via the fuel pump for secondary cooling of the inner coolant. The cooled inner coolant then enters the heat exchanger for further heat exchange before finally entering the combustion chamber.
[0005] Furthermore, the outer coolant and the inner coolant flow in opposite directions.
[0006] Furthermore, the inner cooling circuit also includes an electromagnetic pump, which is located on the inner cooling pipeline.
[0007] Furthermore, the outer cooling channel and the inner cooling channel are arranged at intervals, and one inner cooling channel corresponds to at least one outer cooling channel.
[0008] Furthermore, the outer cooling channel and the inner cooling channel are configured in a one-to-one correspondence.
[0009] Furthermore, the outer and inner cooling channels are arranged alternately.
[0010] Furthermore, the cross-sections of the outer cooling channel and the inner cooling channel are rectangular, circular, or semi-circular.
[0011] Furthermore, the cross-section of the outer cooling channel gradually increases from one end to the other.
[0012] Furthermore, the outer cooling channel is a continuous flow channel, and the inner cooling channel is a direct flow channel.
[0013] Furthermore, the outer coolant is hydrocarbon fuel, and the inner coolant is liquid metal.
[0014] The technical solution of this invention has the following advantages:
[0015] 1. The present invention provides a dual-channel cooling system for a scramjet engine, comprising: a fuel tank containing an outer layer of coolant, the fuel tank being connected to a fuel pump; a combustion chamber containing an outer layer cooling channel and an inner layer cooling channel within its wall; and an inner layer cooling circuit comprising a heat exchanger and an inner layer cooling pipe, wherein the inner layer coolant in the inner layer cooling pipe passes through the inner layer cooling channel to perform primary cooling on the wall of the combustion chamber, and the heat exchanger performs heat exchange on the inner layer coolant; the outer layer coolant in the fuel tank enters the outer layer cooling channel through the fuel pump to perform secondary cooling on the inner layer coolant, the cooled inner layer coolant then enters the heat exchanger for heat exchange, and finally enters the combustion chamber.
[0016] In practical application, this dual-channel cooling system for the supercharged ramjet engine works by first circulating the inner coolant within the inner cooling circuit along the combustion chamber walls and inner cooling pipes. The inner cooling circuit is a closed loop. As the inner coolant passes through the inner cooling channels, it provides primary cooling to the combustion chamber walls. The cooled inner coolant then flows back to the heat exchanger for heat exchange. Meanwhile, the outer coolant in the fuel tank enters the outer cooling channels via the fuel pump, providing secondary cooling to the inner coolant. The cooled inner coolant then enters the heat exchanger for further heat exchange before finally entering the combustion chamber.
[0017] By first using the inner coolant to perform primary cooling of the scramjet engine wall, and then using the outer coolant to perform secondary cooling of the inner coolant, the chemical reaction of the outer coolant's decomposition can be transferred from the cooling channels on the wall to the heat exchanger between the inner and outer coolants. In this way, coking of the outer coolant occurs in a reusable heat exchanger, avoiding the coking phenomenon in traditional regenerative cooling channels. At the same time, this two-stage cooling process has a better wall cooling effect compared to the single-channel cooling process of the inner coolant, and the outer coolant at the cooling channel outlet has also completed the preheating process, realizing the recovery and utilization of combustion chamber heat.
[0018] 2. The dual-channel cooling system for scramjet engines provided by this invention has outer and inner coolants flowing in opposite directions. This counter-current arrangement of the inner and outer coolants in the cooling channels ensures that the highest temperature point on the engine wall does not exceed the limit, meaning the inner coolant does not exceed the limit at the outlet of the inner cooling channel, thus achieving effective thermal protection of the engine wall.
[0019] 3. The dual-channel cooling system for scramjet engines provided by this invention has an outer cooling channel whose cross-section gradually increases from one end to the other. This ensures that the heat absorption of the engine wall is approximately equal everywhere, thus guaranteeing good temperature uniformity of the wall and making the overall wall temperature tend to be consistent.
[0020] 4. The dual-channel cooling system for scramjet engines provided by this invention comprises an outer cooling channel that is a continuous flow channel and an inner cooling channel that is a direct-flow channel. The use of different types of flow channels in the outer cooling channel can enhance the heat exchange effect within the outer cooling channel, thus facilitating the realization of enhanced heat transfer within the outer cooling channel.
[0021] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description
[0022] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0023] Figure 1 This is a schematic diagram of the dual-channel cooling system for a scramjet engine provided by the present invention;
[0024] Figure 2A schematic diagram of the outer and inner cooling channels of the dual-channel cooling system for a scramjet engine provided for the invention;
[0025] Figure 3 A schematic diagram of the structure of an outer cooling channel and an inner cooling channel of a dual-channel cooling system for a scramjet engine provided for the invention;
[0026] Figure 4 A schematic diagram of the structure of the dual-channel cooling system for a scramjet engine provided for the invention, consisting of two outer cooling channels and one inner cooling channel;
[0027] Figure 5 A schematic diagram of the structure of the three outer cooling channels and one inner cooling channel of the dual-channel cooling system for a scramjet engine provided for the invention;
[0028] Figure 6 A schematic diagram of the structure of the dual-channel cooling system for a scramjet engine provided for the invention, showing the staggered arrangement of the outer and inner cooling channels;
[0029] Figure 7 A schematic diagram of the outer cooling channel of the dual-channel cooling system for a scramjet engine provided for the invention.
[0030] Explanation of reference numerals in the attached figures:
[0031] 1. Fuel tank; 2. Outer coolant; 3. Fuel pump; 4. Combustion chamber; 5. Outer cooling channel; 6. Inner cooling channel; 7. Inner coolant; 8. Heat exchanger; 9. Inner cooling piping; 10. Electromagnetic pump. Detailed Implementation
[0032] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.
[0033] In the description of this disclosure, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this disclosure, "a plurality of" means two or more, unless otherwise explicitly specified.
[0034] In the description of this disclosure, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joint" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or connections that allow for communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.
[0035] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.
[0036] The following disclosure provides numerous different embodiments or examples for implementing various structures of this disclosure. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of this disclosure. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this disclosure, but those skilled in the art will recognize the application of other processes and / or the use of other materials.
[0037] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.
[0038] Please see Figures 1 to 4 As shown, the present invention provides a dual-channel cooling system for a scramjet engine, comprising: a fuel tank 1, wherein an outer layer coolant 2 is provided in the fuel tank 1, and the fuel tank 1 is connected to a fuel pump 3; a combustion chamber 4, wherein an outer layer cooling channel 5 and an inner layer cooling channel 6 are provided in the wall of the combustion chamber 4; an inner layer cooling circuit, wherein the cooling circuit includes a heat exchanger 8 and an inner layer cooling pipe 9, wherein the inner layer coolant 7 in the inner layer cooling pipe 9 performs primary cooling on the wall of the combustion chamber 4 through the inner layer cooling channel 6, and uses the heat exchanger 8 to exchange heat with the liquid metal; the outer layer coolant 2 in the fuel tank 1 enters the outer layer cooling channel 5 through the fuel pump 3 to perform secondary cooling on the inner layer coolant 7, the cooled inner layer coolant 7 enters the heat exchanger 8 for heat exchange, and finally enters the combustion chamber 4.
[0039] In practical application, this dual-channel cooling system for the supercharged ramjet engine first flows through the inner cooling circuit 7, which is a closed-loop system, through the combustion chamber 4 and the inner cooling pipes 9. The inner cooling circuit 7 provides primary cooling to the combustion chamber 4 wall as it passes through the inner cooling channel 6. After primary cooling, the inner cooling fluid 7 flows back to the heat exchanger 8 for heat exchange. The outer cooling fluid 2 in the fuel tank 1 enters the outer cooling channel 5 via the fuel pump 3 for secondary cooling of the inner cooling fluid 7. The cooled inner cooling fluid 7 then enters the heat exchanger 8 for further heat exchange before finally entering the combustion chamber 4.
[0040] By first using the inner coolant 7 to perform primary cooling on the scramjet engine wall, and then using the outer coolant 2 to perform secondary cooling on the inner coolant 7, the chemical reaction of the outer coolant 2 undergoing decomposition can be transferred from the cooling channel on the wall to the heat exchanger 8 between the inner coolant 7 and the outer coolant 2. In this way, coking of the outer coolant 2 occurs in the replaceable heat exchanger 8, avoiding the coking phenomenon in the traditional regenerative cooling channel. At the same time, this two-stage cooling process has a better wall cooling effect than the single-channel cooling process of the inner coolant 7, and the outer coolant 2 at the cooling channel outlet has also completed the preheating process, realizing the recovery and utilization of heat in the combustion chamber 4.
[0041] The inner coolant 7 is used to absorb heat in the combustion chamber 4 to cool the engine wall. The outer coolant 2 absorbs heat from the inner coolant 7 and is finally injected back into the combustion chamber 4, so that the heat in the combustion chamber 4 can be recovered and reused. The outer coolant 2 and the inner coolant 7 are arranged in a counter-current manner in the cooling channel. That is, the flow directions of the outer coolant 2 and the inner coolant 7 are opposite.
[0042] The counter-current arrangement of the inner coolant 7 and the outer coolant 2 in the cooling channel ensures that the highest temperature point on the engine wall does not exceed the limit. That is, the temperature of the inner coolant 7 at the outlet of the inner cooling channel 6 does not exceed the limit, thus achieving effective thermal protection of the engine wall.
[0043] In some optional embodiments, the inner cooling circuit further includes an electromagnetic pump 10, which is disposed on the inner cooling pipe 9. The electromagnetic pump 10 allows the inner cooling fluid 7 in the inner cooling circuit to flow within the inner cooling pipe 9 and the inner cooling channel 6, providing a power source for the flow of the inner cooling fluid 7.
[0044] In some optional embodiments, the outer cooling channel 5 and the inner cooling channel 6 are arranged at intervals, and the outer cooling channel 5 and the inner cooling channel 6 adopt a structure with a common wall surface. This arrangement has the characteristics of high-efficiency heat transfer and lightweight structure; and one inner cooling channel 6 corresponds to at least one outer cooling channel 5.
[0045] That is, one inner cooling channel 6 can correspond to one outer cooling channel 5. Of course, one inner cooling channel 6 can correspond to multiple outer cooling channels 5. Specifically, it can be set according to the actual situation.
[0046] In some alternative embodiments, the outer cooling channel 5 and the inner cooling channel 6 are arranged in a one-to-one correspondence; of course, the outer cooling channel 5 and the inner cooling channel 6 are arranged alternately. Specifically, it can be set according to the actual situation.
[0047] In some optional embodiments, the cross-sections of the outer cooling channel 5 and the inner cooling channel 6 are rectangular, circular, or semi-circular.
[0048] In some optional embodiments, the cross-section of the outer cooling channel 5 gradually increases from one end to the other. This ensures that the heat absorption of the engine wall is approximately equal everywhere, thus guaranteeing good temperature uniformity of the wall and making the overall wall temperature tend to be consistent.
[0049] The inner cooling channel 6 retains a constant cross-sectional shape along the fluid flow direction, while the outer cooling channel 5 may retain a constant cross-sectional shape along the fluid flow direction, or its cross-sectional area may gradually increase along the fluid flow direction. Specifically, it can be set according to the actual situation.
[0050] In some optional embodiments, the outer cooling channel 5 is a continuous flow channel, and the inner cooling channel 6 is a direct flow channel. The continuous flow channel can be a direct flow channel, a serpentine flow channel, a zigzag flow channel, etc.
[0051] Alternatively, the outer cooling channel 5 can be a discontinuous flow channel, such as an airfoil flow channel.
[0052] The outer cooling channel 5 adopts different types of flow channels, which can enhance the heat exchange effect in the outer cooling channel 5 and help to achieve the enhanced heat transfer phenomenon in the outer cooling channel 5.
[0053] In this embodiment, the outer coolant 2 is hydrocarbon fuel, and the inner coolant 7 is liquid metal. Specifically, the liquid metal is liquid lithium, gallium-based alloy, or sodium-potassium alloy.
[0054] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.
Claims
1. A dual passage cooling system for a scramjet engine, characterized in that, include: A fuel tank (1) is provided with an outer layer of coolant (2) and the fuel tank (1) is connected to a fuel pump (3); Combustion chamber (4), wherein the wall of combustion chamber (4) is provided with an outer cooling channel (5) and an inner cooling channel (6); The inner cooling circuit includes a heat exchanger (8) and an inner cooling pipe (9). The inner cooling liquid (7) in the inner cooling pipe (9) is cooled firstly on the wall of the combustion chamber (4) through the inner cooling channel (6), and the heat exchanger (8) is used to exchange heat with the inner cooling liquid (7). The outer layer coolant (2) in the fuel tank (1) enters the outer layer cooling channel (5) through the fuel pump (3) to perform secondary cooling on the inner layer coolant (7). The cooled inner layer coolant (7) enters the heat exchanger (8) for heat exchange and finally enters the combustion chamber (4). The outer layer coolant (2) and the inner layer coolant (7) flow in opposite directions; The outer cooling channel (5) and the inner cooling channel (6) are arranged at intervals, and one inner cooling channel (6) corresponds to at least one outer cooling channel (5); The outer cooling channel (5) and the inner cooling channel (6) are configured in a one-to-one correspondence.
2. The dual passage cooling system of a scramjet engine according to claim 1, wherein, The inner cooling circuit also includes an electromagnetic pump (10), which is located on the inner cooling pipe (9).
3. The dual passage cooling system of a scramjet engine according to claim 2, wherein, The outer cooling channel (5) and the inner cooling channel (6) are arranged alternately.
4. The dual passage cooling system of a scramjet engine according to claim 3, wherein, The cross-sections of the outer cooling channel (5) and the inner cooling channel (6) are rectangular, circular, or semi-circular.
5. The dual passage cooling system of a scramjet engine as recited in claim 4, wherein, The cross-section of the outer cooling channel (5) gradually increases from one end to the other.
6. The dual passage cooling system of a scramjet engine according to any one of claims 2-5, wherein, The outer cooling channel (5) is a continuous flow channel, and the inner cooling channel (6) is a direct flow channel.
7. The dual-channel cooling system for a scramjet engine according to claim 6, characterized in that, The outer coolant (2) is hydrocarbon fuel, and the inner coolant (7) is liquid metal.