Liquid rocket engine enhanced heat transfer thrust chamber barrel structure

Abstract

The application relates to the field of liquid rocket engines, and particularly discloses a liquid rocket engine reinforced heat exchange type thrust chamber body structure. The thrust chamber body structure comprises a groove inner wall and an outer wall, and the inner side of the groove inner wall is provided with a plurality of reinforced heat exchange ribs which are distributed along the circumference of the inner wall. The heat exchange area of the thrust chamber body is increased, the boundary layer near the inner wall surface is disturbed and destroyed, and therefore the heat exchange capacity of the cooling jacket of the thrust chamber body is improved.

Description

Technical Field

[0001] This invention patent relates to a novel enhanced thrust chamber body structure and engine for liquid rocket engines, which can be used in the field of liquid rocket engines. Background Technology

[0002] For an expander cycle engine, the thrust chamber cooling jacket serves as both a thermal protection structure to prevent the combustion chamber walls from being ablated and damaged, and a heater structure to heat the propellant and provide the energy needed for power generation. The propellant needs to achieve the highest possible temperature rise within the thrust chamber cooling jacket to provide sufficient energy to drive the propellant turbine. Therefore, improving the heat exchange capacity of the thrust chamber cooling jacket is crucial for enhancing the performance of an expander cycle engine.

[0003] The most direct and effective way to improve the heat exchange capacity of the thrust chamber cooling jacket is to increase the heat exchange area, usually by extending the length of the thrust chamber. However, this will significantly increase the weight and structural size of the engine thrust chamber, reduce the thrust-to-weight ratio, and thus affect the overall performance of the engine. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings of existing technologies by providing a novel enhanced heat exchange type thrust chamber body cooling jacket structure design. By increasing the heat exchange area of ​​the thrust chamber body and disturbing and destroying the near-wall boundary layer, the heat exchange capacity of the thrust chamber body cooling jacket is improved.

[0005] Specifically, this patent designs a novel enhanced heat exchange type thrust chamber cooling jacket structure by adding enhanced heat exchange ribs to the inner surface of the inner wall, increasing the heat exchange area of ​​the thrust chamber body, disturbing and destroying the boundary layer near the wall, and improving the heat exchange capacity of the thrust chamber cooling jacket.

[0006] The technical solution adopted in this application is as follows:

[0007] A liquid rocket engine enhanced heat exchange thrust chamber body structure includes an inner wall, an outer wall, and multiple cooling ribs connecting the inner wall and the outer wall. Multiple enhanced heat exchange ribs distributed circumferentially along the inner wall are connected to the inner side of the inner wall.

[0008] The enhanced heat exchange ribs are evenly distributed on the inner surface of the inner wall.

[0009] The enhanced heat exchange ribs can be configured as A non-cooled enhanced heat exchange ribs, that is, the arrangement position of the enhanced heat exchange ribs corresponds to that of the cooling ribs.

[0010] Alternatively, the enhanced heat exchange ribs can be configured as B-type active cooling enhanced heat exchange ribs, meaning that the arrangement of the enhanced heat exchange ribs corresponds to the cooling channels.

[0011] The axial length L of the enhanced heat exchange rib can be determined based on the thrust chamber body length and the required heat exchange capacity. It is typically designed to be equal to the length of the cylindrical section of the thrust chamber body.

[0012] The height of the enhanced heat exchange ribs is designed to gradually increase along the axial direction to prevent the boundary layer from developing and recovering along the axial direction, and the boundary layer thickness does not exceed the height of the enhanced heat exchange ribs.

[0013] The increased heat exchange area can be calculated based on the structural design of the enhanced heat exchange ribs, and the increased heat exchange capacity can be calculated based on the rib efficiency.

[0014] In summary, this application includes at least the following beneficial technical effects:

[0015] 1) Compared with the commonly used method of extending the length of the cylindrical section to enhance heat exchange, the weight of the thrust chamber body can be effectively reduced, the size of the structure can be reduced, and the structural rigidity can be improved;

[0016] 2) The enhanced heat exchange fin structure is easy to process;

[0017] 3) Enhanced heat exchange ribs can significantly increase the heat exchange area of ​​the thrust chamber cooling jacket and improve the heat exchange capacity;

[0018] 4) The height design of the heat exchange fins can increase the disturbance and damage to the boundary layer of the gas side wall, thereby enhancing the convective heat transfer effect. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the thrust chamber body cooling jacket structure in the embodiments of this application;

[0020] Figure 2 for Figure 1 A magnified schematic diagram of a portion of the structure.

[0021] Explanation of reference numerals in the attached diagram: 1. Inner wall of the groove; 2. Outer wall; 3. Cooling rib; 4. Enhanced heat exchange rib. Detailed Implementation

[0022] The present application will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0023] This application discloses an enhanced heat exchange type thrust chamber cooling jacket structure for a liquid rocket engine, referring to... Figure 1 and Figure 2 It includes an inner wall 1, an outer wall 2, and multiple cooling ribs 3 connecting the inner wall 1 and the outer wall 2. The cooling ribs 3 on the outer surface of the inner wall 1 and the inner surface of the outer wall 2 cooperate to form a cooling channel, which together form a cooling jacket. The cooling ribs 3 are evenly distributed on the outer surface of the inner wall 1 and the outer wall 2. Multiple heat exchange reinforcing ribs 4 are connected to the inner side of the inner wall 1 and are evenly distributed along the inner circumference of the inner side of the inner wall 1.

[0024] The height of the enhanced heat exchange rib 4 is its radial length along the inner wall 1 of the groove. The height j of the enhanced heat exchange rib 4 gradually increases along the gas flow direction, j = ax + j1, where j1 is the initial height of the enhanced heat exchange rib; a is the height increase coefficient of the enhanced heat exchange rib, a = (j2 - j1) / L, j2 is the final rib height of the enhanced heat exchange rib, and the final rib height of the enhanced heat exchange rib 4 exceeds the boundary layer thickness, where L is the length of the straight section of the thrust chamber body. By uniformly varying the rib height of the enhanced heat exchange rib 4 and setting the final rib height, the disturbance and disruption of the boundary layer on the gas sidewall are increased, thereby enhancing the convective heat transfer effect.

[0025] The axial length L of the reinforcing heat exchange rib 4 can be determined based on the thrust chamber body length and the required heat exchange. It is typically designed to be equal to the length of the cylindrical section of the thrust chamber body, making the overall thrust chamber structure easier to manufacture and reducing the risk of the reinforcing heat exchange rib 4 burning out. The increased heat exchange area can be calculated based on the structural design of the reinforcing heat exchange rib 4, and the increased heat exchange can be calculated based on the rib efficiency.

[0026] The enhanced heat exchange rib 4 can be configured as a non-cooling enhanced heat exchange rib, that is, the enhanced heat exchange rib 4 is arranged in a position corresponding to the cooling rib 3. The two ends of the enhanced heat exchange rib 4 along the radial direction of the inner wall 1 of the groove are the lower bottom and the upper bottom, respectively. The circumferential dimension of the cooling rib 3 along the inner wall 1 is the width of the cooling rib 3. The lower bottom is located on the side of the upper bottom facing the axis of the inner wall 1. The width s of the upper bottom of the enhanced heat exchange rib 4 is equal to the width t of the lower bottom, and is equal to the width b of the cooling rib 3, that is, s = t = b.

[0027] Alternatively, the enhanced heat exchange rib 4 can be configured as an active cooling enhanced heat exchange rib (B type). The enhanced heat exchange rib 4 is arranged alternately with the cooling rib 3, and its arrangement is directly opposite the cooling channel formed by two adjacent cooling ribs 3. The two ends of the enhanced heat exchange rib 4 along the radial direction of the inner wall 1 of the groove are the upper bottom and the lower bottom, respectively. The lower bottom is located on the side of the upper bottom facing the axis of the inner wall 1 of the groove. The width s of the upper bottom of the enhanced heat exchange rib 4 is greater than the width t of the lower bottom, and less than or equal to the width k of the cooling channel, i.e., t... <s≤k。

[0028] By enhancing the positional relationship between the heat exchange rib 4 and the cooling rib 3, and by setting the shape of the enhanced heat exchange rib 4 according to the positional relationship, the enhanced heat exchange rib 4 can achieve a good heat exchange effect in both the above-mentioned A non-cooling enhanced heat exchange rib and B active cooling enhanced heat exchange rib modes.

[0029] The implementation principle of this application is as follows: When the thrust chamber cooling jacket structure of this application is in working condition, the propellant can flow in the cooling jacket, and the high-temperature gas flows on the inner side of the groove inner wall. By adding the enhanced heat exchange rib 4, the contact area between the high-temperature gas and the propellant is increased through the enhanced heat exchange rib 4, and the variable rib height design of the enhanced heat exchange rib 4 can increase the disturbance and damage to the boundary layer of the gas side wall, thereby enhancing the heat exchange effect.

[0030] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A liquid rocket engine augmented heat transfer thrust chamber case structure, characterized by: The groove inner wall (1), the outer wall (2), the groove inner wall (1) outside with a plurality of cooling ribs (3), cooling ribs (3) and the outer wall (2) constitute the cooling channel of coolant circulation, the inner side of the groove inner wall (1) is connected with a plurality of along the inner wall (1) circumferentially distributed enhanced heat transfer rib (4); The height j of the enhanced heat transfer rib (4) gradually increases along the gas flow direction, j=ax+j1, wherein j1 is the initial height of the enhanced heat transfer rib (4); A is the height increase coefficient of the enhanced heat transfer rib; A=(j2-j1) / L, j2 is the final rib height of the enhanced heat transfer rib, and L is the length of the straight section of the groove inner wall (1); The final rib height j2 is not less than the thickness of the boundary layer of the groove inner wall (1); The two ends of the enhanced heat transfer rib (4) along the radial direction of the inner wall (1) are the lower bottom and the upper bottom, respectively, and the upper bottom is located on the side of the lower bottom towards the axis of the inner wall (1); The size of the cooling rib (3) along the circumferential direction of the inner wall (1) is the width of the cooling rib (3); The lower bottom is located on the side of the upper bottom towards the axis of the inner wall (1), the width s of the upper bottom of the enhanced heat transfer rib (4) is equal to the width t of the lower bottom, and is equal to the width b of the cooling rib (3), that is, s=t=b; Or, the width s of the upper bottom of the enhanced heat transfer rib (4) is greater than the width t of the lower bottom, and is less than or equal to the width k of the cooling channel, that is, t<s≤k; Along the axis direction of the groove inner wall (1), the width of the upper bottom and the width t of the lower bottom of different enhanced heat transfer ribs (4) are constant; The enhanced heat transfer rib (4) is arranged in staggered with the cooling rib (3), and the enhanced heat transfer rib is arranged opposite to the cooling channel formed by the two adjacent cooling ribs (3).

2. A liquid rocket engine augmented heat transfer thrust chamber case structure as in claim 1, wherein: The height of the enhanced heat transfer rib (4) is the length of the enhanced heat transfer rib (4) along the radial direction of the groove inner wall (1), and the height of the enhanced heat transfer rib (4) increases along the gas flow direction; The length of the enhanced heat transfer rib (4) is the same as the straight section of the groove inner wall (1).

3. A liquid rocket engine augmented heat transfer thrust chamber case structure as in claim 1, wherein: The number n1 of the enhanced heat transfer rib (4) is the same as the number n0 of the cooling rib (3).

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