Nozzle structure and nuclear rocket engine system

Abstract

The present application discloses a nozzle structure and a nuclear rocket engine system, wherein the nozzle structure comprises: a nozzle body, a plurality of regenerative cooling channels for coolant to pass through between the inner wall and the outer wall of the nozzle body, the nozzle body comprises a first part, a second part and a throat connecting the first part and the second part, the second part is used to be connected to the nuclear rocket engine system; a first spoiler assembly is arranged on the first part and located in each regenerative cooling channel, the first spoiler assembly comprises a first bottom spoiler rib and a first side spoiler rib, the first bottom spoiler rib is arranged on the bottom wall of the regenerative cooling channel, the first side spoiler rib is arranged on the side wall of the regenerative cooling channel, and is distributed on at least one side of the first bottom spoiler rib along the length direction of the regenerative cooling channel. By adopting the present application, the cooling effect of the regenerative cooling channel is effectively improved, thereby improving the heat bearing limit of the nozzle.

Description

Technical Field

[0001] The present application relates to the field of nuclear rocket technology, and in particular to a nozzle structure and a nuclear rocket engine system. Background Art

[0002] Regenerative cooling is a widely used cooling method in liquid rocket engines. For nuclear rockets, this involves using the propellant itself as a coolant. Before entering the core, the propellant flows into regenerative cooling channels, absorbing heat from the nozzle walls. It is then heated in the core and ejected through the nozzle to generate thrust.

[0003] At present, the regenerative cooling channel of nuclear rocket engines usually adopts a rectangular channel structure. Due to the high-speed flow of coolant through the channel, there is a problem of insufficient heat exchange between coolants, which affects the cooling effect, making it difficult to further improve the overall performance of the nuclear rocket. Summary of the Invention

[0004] In order to enhance the cooling effect of the regenerative cooling channel, the present application provides a nozzle structure and a nuclear rocket engine system, which adopt the following technical solutions:

[0005] In a first aspect, the present application provides a nozzle structure, comprising:

[0006] a nozzle body having a plurality of regenerative cooling channels between an inner wall and an outer wall thereof for passing a coolant, the nozzle body comprising a first portion, a second portion, and a throat connecting the first portion and the second portion, the second portion being configured to be connected to a nuclear rocket engine system;

[0007] A first spoiler assembly is arranged on the first part and is located in each of the regenerative cooling channels. The first spoiler assembly includes a first bottom spoiler rib and a first side spoiler rib. The first bottom spoiler rib is arranged on the bottom wall of the regenerative cooling channel. The first side spoiler rib is arranged on the side wall of the regenerative cooling channel and is distributed on at least one side of the first bottom spoiler rib along the length direction of the regenerative cooling channel.

[0008] Optionally, the first bottom spoiler rib is streamlined, and a surface of the first bottom spoiler rib is smoothly connected to the bottom wall of the regenerative cooling channel.

[0009] Optionally, a size ratio between the first side spoiler rib and the regenerative cooling channel satisfies the following relationship:

[0010] 0.1d<h s <0.2d;

[0011] Wherein, d is the width of the regenerative cooling channel, h sis the maximum dimension of the first side spoiler rib in the width direction of the regeneration cooling channel.

[0012] Optionally, a size ratio between the first bottom spoiler rib and the regenerative cooling channel satisfies the following relationship:

[0013] 0.05h<h b <0.1h;

[0014] Wherein, h is the height of the regenerative cooling channel, h b is the maximum dimension of the first bottom spoiler rib in the height direction of the regenerative cooling channel.

[0015] Optionally, a second spoiler assembly is further included, which is provided on the second portion and located in each of the regenerative cooling channels, wherein the second spoiler assembly includes a second bottom spoiler rib and a second side spoiler rib, wherein the second bottom spoiler rib is provided on the bottom wall of the regenerative cooling channel, and the second side spoiler rib is provided on the side wall of the regenerative cooling channel and is distributed on at least one side of the second bottom spoiler rib along the length direction of the regenerative cooling channel;

[0016] There is a cavity between the second bottom spoiler rib and the bottom wall of the regenerative cooling channel. The second bottom spoiler rib is provided with a through hole, and the coolant can enter the cavity through the through hole when flowing along the regenerative cooling channel; the bottom wall of the regenerative cooling channel is set to a porous structure at a position corresponding to the cavity, so that the coolant in the cavity can penetrate into the nozzle structure through the porous structure.

[0017] Optionally, the shape and size of the second spoiler component are the same as those of the first spoiler component.

[0018] Optionally, the throat portion has a first plane, and the first plane is a cross section corresponding to a position where the inner diameter of the throat portion is minimum;

[0019] The first portion has a second plane and a third plane parallel to the first plane, the distance between the second plane and the first plane is 20 mm, the distance between the third plane and the first plane is 50 mm, and the first spoiler component is located between the second plane and the third plane;

[0020] The second portion has a fourth plane and a fifth plane parallel to the first plane, the distance between the fourth plane and the first plane is 50 mm, the distance between the fifth plane and the first plane is 100 mm, and the second spoiler component is located within the fourth plane and the fifth plane.

[0021] Optionally, the porous structure is made of ceramic.

[0022] Optionally, a plurality of groups of the first spoiler components are arranged at intervals in the regeneration cooling channel.

[0023] In a second aspect, the present application provides a nuclear rocket engine system, comprising the nozzle structure described in any one of the first aspects.

[0024] As mentioned above, the present application sets a first spoiler component at a position near the throat of the first part. During the flow of the coolant along the regenerative cooling channel, the fluid near the bottom wall of the regenerative cooling channel is affected by the first bottom spoiler rib and generates a component velocity toward the top wall of the channel, which is mixed with the fluid in the upper part of the channel, so that the fluid is mixed and heat exchanged in the height direction of the channel; at the same time, the fluid is affected by the first side spoiler rib and generates a component velocity toward the center of the channel, so that the fluid enhances mixing in the width direction of the channel and thus enhances heat exchange.

[0025] Therefore, the present application combines the first bottom spoiler ribs and the first side spoiler ribs to enhance the convective mass transfer and turbulent mixing of the fluid as it flows through the first spoiler assembly along the regenerative cooling channel. The fluid is fully mixed and heat-exchanged in the height and width dimensions of the channel, thereby enhancing the cooling effect on the throat when the fluid passes through the throat after passing through the first spoiler assembly, effectively improving the heat bearing limit of the nozzle throat. On the other hand, since the heat bearing limit of the nozzle is enhanced, it can withstand higher reactor core outlet temperatures, which is beneficial to improving the thrust of the nuclear rocket engine and ensuring long-term stable operation of the thrust chamber. Combined with the long life of the nuclear rocket engine reactor, the important advantage of the long service life of the nuclear rocket engine is fully reflected. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solution of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without exceeding the scope of protection required by this application.

[0027] Figure 1 This is a schematic diagram of the overall structure of the nozzle structure provided in the embodiment of the present application;

[0028] Figure 2 yes Figure 1 A front view of the center nozzle structure;

[0029] Figure 3 yes Figure 1 sectional view of

[0030] Figure 4 is a schematic diagram of the three-dimensional structure of the first spoiler component in the regenerative cooling channel;

[0031] Figure 5 is a cross-sectional schematic diagram of the regenerative cooling channel at the first portion;

[0032] Figure 6 is a schematic longitudinal section of the regenerative cooling channel at the first portion;

[0033] Figure 7 is a schematic diagram of the three-dimensional structure of the second spoiler component in the regenerative cooling channel;

[0034] Figure 8 yes Figure 7 A partial schematic diagram of the position of the second bottom spoiler rib.

[0035] In the figure, 1. nozzle body; 100. regenerative cooling channel; 11. first part; 110. cavity; 12. second part; 120. porous structure; 13. throat; 2. first spoiler assembly; 21. first bottom spoiler rib; 22. first side spoiler rib; 3. second spoiler assembly; 31. second bottom spoiler rib; 311. through hole; 32. second side spoiler rib; S1. first plane; S2. second plane; S3. third plane; S4. fourth plane; S5. fifth plane. DETAILED DESCRIPTION

[0036] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood broadly. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections, or interconnected connections; direct connections or indirect connections through an intermediary; and internal connections between two components or interactions between two components. Those skilled in the art will understand the specific meanings of these terms in this application based on specific circumstances.

[0037] The following is a clear and complete description of the technical solution of this application in conjunction with the drawings in the embodiments of this application. Obviously, the embodiments described are part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without making any creative efforts are within the scope of protection of this application.

[0038] During the operation of a nuclear rocket's regenerative cooling system, coolant flows through the regenerative cooling channels into the reactor core, is heated by the core, and is then ejected through the cavity inside the nozzle. Because the temperature in each regenerative cooling channel is higher near the nozzle interior, and the coolant flows directly through the channel at high speed, this results in a stable coolant temperature stratification within each channel. Specifically, the temperature near the nozzle inner wall is higher, while the temperature away from the nozzle inner wall is lower. This prevents effective heat exchange between the coolants, thus affecting the cooling effect.

[0039] Reference Figure 1 、 Figure 2 and Figure 3 , is a nozzle structure disclosed in an embodiment of the present application, which includes a nozzle body 1 and a first spoiler component 2.

[0040] The nozzle body 1 has a certain wall thickness. A regenerative cooling channel 100 for coolant is formed between its inner and outer walls. The internal cavity of the nozzle body 1 serves as a channel for high-temperature propellant. Along the axial direction of the nozzle body 1, the cross-section of the nozzle body 1 gradually contracts and then expands. For ease of illustration, the nozzle body 1 is divided into a first section 11, a second section 12, and a throat 13. The end of the second section 12 is used to connect to the nuclear rocket engine system. The throat 13 connects between the first and second sections 11, 12, and represents the narrowest portion of the nozzle body 1's inner diameter.

[0041] Multiple regenerative cooling channels 100 are provided along the circumference of the nozzle body 1. Each regenerative cooling channel 100 is an independent channel, and each regenerative cooling channel 100 has an approximately rectangular cross-section. For ease of description, the wall of the regenerative cooling channel 100 adjacent to the interior of the nozzle body 1 is referred to as the bottom wall, the wall opposite the bottom wall is referred to as the top wall, and the remaining two parallel walls are referred to as side walls. The side walls of the regenerative cooling channel 100 are made of zirconium-copper alloy, and the bottom wall is made of electroformed nickel.

[0042] It should be understood that, according to the flow direction of the coolant and the flow direction of the high-temperature propellant, the end of the first part 11 away from the throat 13 is the inlet of the regenerative cooling channel 100, and the end of the second part 12 away from the throat 13 is the outlet of the regenerative cooling channel 100.

[0043] Reference Figure 4 、 Figure 5 and Figure 6 The first spoiler assembly 2 is disposed on the first portion 11 and is located near the throat 13. At least one set of the first spoiler assembly 2 is provided in each regenerative cooling channel 100. The first spoiler assembly 2 includes a first bottom spoiler rib 21 and a first side spoiler rib 22. The first bottom spoiler rib 21 is fixedly mounted on the bottom wall of the regenerative cooling channel 100, and the first side spoiler rib 22 is fixedly mounted on the side wall of the regenerative cooling channel 100.

[0044] It should be noted that one first side spoiler rib 22 is provided on each of a set of side walls of the regenerative cooling channel 100, and two first side spoiler ribs 22 are arranged opposite each other. The first side spoiler ribs 22 are distributed on at least one side of the first bottom spoiler rib 21 along the length direction of the regenerative cooling channel 100. Optionally, in a possible implementation form of the embodiment of the present application, the first side spoiler ribs 22 are distributed on both sides of the first bottom spoiler rib 21 along the length direction of the regenerative cooling channel 100, and a group of first side spoiler ribs 22 is provided on each side, that is, each group of first spoiler assemblies 2 includes one first bottom spoiler rib 21 and four first side spoiler ribs 22.

[0045] In the present application, a first spoiler assembly 2 is arranged at a position near the throat of the first part 11. During the flow of the coolant along the regenerative cooling channel 100, the fluid near the bottom wall of the regenerative cooling channel 100 is affected by the first bottom spoiler rib 21 and generates a component velocity toward the top wall of the channel, which is mixed with the fluid in the upper part of the channel, so that the fluid is mixed and heat exchanged in the height direction of the channel; at the same time, the fluid is affected by the first side spoiler rib 22 and generates a component velocity toward the center of the channel, so that the fluid is enhanced in the width direction of the channel and thus enhances heat exchange.

[0046] Therefore, the present application combines the first bottom spoiler rib 21 and the first side spoiler rib 22 to enhance the convective mass transfer and turbulent mixing of the fluid as it flows through the first spoiler assembly 2 along the regenerative cooling channel 100, and the fluid is fully mixed and heat-exchanged in the height and width dimensions of the channel, thereby enhancing the cooling effect on the throat 13 when the fluid passes through the throat 13 after passing through the first spoiler assembly 2, and effectively improving the heat bearing limit of the nozzle throat 13. On the other hand, since the heat bearing limit of the nozzle is enhanced, it can withstand a higher reactor core outlet temperature, which is beneficial to improving the thrust of the nuclear rocket engine and ensuring the long-term stable operation of the thrust chamber. Combined with the long life of the nuclear rocket engine reactor, the important advantage of the long service life of the nuclear rocket engine is fully reflected.

[0047] As an optional technical solution of the embodiment of the present application, refer to Figure 4The first bottom spoiler rib 21 is streamlined, and its surface smoothly connects to the bottom of the regenerative cooling channel 100. It should be understood that the aforementioned streamlined shape refers to the first bottom spoiler rib 21 having a smooth, curved surface facing the top wall of the regenerative cooling channel 100, with both ends of the curved surface smoothly connected to the bottom wall of the channel. For example, the shape of an aircraft wing can be used as a reference. The configuration of the first bottom spoiler rib 21 results in a concave shape on the inner wall of the nozzle structure corresponding to the first bottom spoiler rib 21. This streamlined configuration allows the fluid to smoothly rise along the bottom wall of the channel to the surface of the first bottom spoiler rib 21, mix with the fluid above, and then flow smoothly along the surface after passing the top of the first bottom spoiler rib 21, contacting the bottom wall of the channel.

[0048] Therefore, the streamlined design prevents the formation of vortices at the first bottom spoiler rib 21, reducing the impact on the pressure drop of the fluid within the channel. This reduces the requirements for the coolant pump and reduces the required coolant pump mass, thereby improving the overall specific impulse of the engine. Furthermore, the streamlined design and the provision of the first lateral spoiler ribs 22 prevent excessively low fluid mass flow rates in front of and behind the first bottom spoiler rib 21, ensuring that the coolant fully contacts all areas of the channel bottom wall, enhancing the cooling effect.

[0049] As an optional technical solution of the embodiment of the present application, refer to Figure 5 The size ratio between the first side spoiler rib 22 and the regenerative cooling channel 100 satisfies the following relationship:

[0050] 0.1d<h s <0.2d

[0051] In the above formula, d is the width of the regenerative cooling channel 100, h is s It is the maximum dimension of the first side spoiler rib 22 in the width direction of the regeneration cooling channel 100 .

[0052] h s The size of the first side spoiler ribs 22 is controlled within a certain range to ensure that the first side spoiler ribs 22 have a mixing effect on the fluid in the width direction of the channel while avoiding an increase in the pressure drop loss of the fluid due to their excessive size in the width direction of the channel.

[0053] As an optional technical solution of the embodiment of the present application, refer to Figure 5 The size ratio between the first bottom spoiler rib 21 and the regenerative cooling channel 100 satisfies the following relationship:

[0054] 0.05h<h b <0.1h

[0055] In the above formula, h is the height of the regenerative cooling channel 100, h bIt is the maximum dimension of the first bottom spoiler rib 21 in the height direction of the regenerative cooling channel 100 .

[0056] Similarly, h b The size of the first bottom spoiler rib 21 is controlled within a certain range to ensure that the first bottom spoiler rib 21 has a mixing effect on the fluid in the channel height direction while avoiding an increase in the pressure drop loss of the fluid due to its excessive size in the channel height direction.

[0057] As an optional technical solution of the embodiment of the present application, refer to Figure 6 and Figure 7 The second portion 12 is also provided with a second spoiler assembly 3, located near the throat 13. At least one second spoiler assembly 3 is provided in each regenerative cooling channel 100. The second spoiler assembly 3 includes a second bottom spoiler rib 31 and a second side spoiler rib 32. The second bottom spoiler rib 31 is fixedly mounted on the bottom wall of the regenerative cooling channel 100, and the second side spoiler rib 32 is fixedly mounted on the side wall of the regenerative cooling channel 100.

[0058] It should be noted that the shape, size, arrangement, and dimensions of the second spoiler assembly 3 are identical to those of the first spoiler assembly 2. The second bottom spoiler ribs 31 are streamlined, and a cavity 110 is formed between the second bottom spoiler ribs 31 and the bottom wall of the regenerative cooling channel 100. The second spoiler assembly 3 differs from the first spoiler assembly 2 in that through-holes 311 are provided in the portion of the second bottom spoiler ribs 31 facing the incoming flow direction, allowing coolant to enter the cavity 110 through the through-holes 311 as it flows along the regenerative cooling channel 100. Furthermore, a porous structure 120 is provided on the bottom wall of the regenerative cooling channel 100 corresponding to the cavity 110, allowing the coolant in the cavity to penetrate into the nozzle structure through the porous structure 120 under pressure.

[0059] The provision of the second spoiler assembly 3 not only further enhances the convective mass transfer and turbulent mixing of the fluid within the regenerative cooling channel 100, thereby improving the cooling effect, but more importantly, by providing through-holes 311 in the second bottom spoiler rib 31, when part of the fluid passes through the porous structure 120 and enters the nozzle, the low-temperature fluid forms a liquid film under the action of the high-temperature propellant. The liquid film adheres to the inner wall of the nozzle and can flow toward the throat 13, further reducing the temperature at the throat 13 and improving the heat-bearing limit of the throat 13.

[0060] Optionally, the porous structure 120 may be made of porous ceramic material. Ceramic material has stable chemical properties under high temperature conditions, ensuring the heat-bearing capacity of the nozzle.

[0061] As an optional technical solution of the embodiment of the present application, refer to Figure 2The plane of the cross section corresponding to the minimum inner diameter of the throat portion 13 is called the first plane S1. A second plane S2 and a third plane S3 are defined on the first portion 11, which are parallel to the first plane S1. The distance from S2 to S1 is 20 mm, and the distance from S3 to S1 is 50 mm. The first spoiler assembly 2 is located in the area between S2 and S3.

[0062] A fourth plane S4 and a fifth plane S5 parallel to the first plane S1 are defined on the second portion 12. The distance between S4 and S1 is 50 mm, the distance between S5 and S1 is 100 mm, and the second spoiler assembly 3 is located in the area between S4 and S5.

[0063] The first spoiler assembly 2 is positioned within a certain range from the first plane S1 of the throat 13 to allow the fluid along the flow time to mix, thereby enhancing the cooling effect of the fluid on the throat 13. The second spoiler assembly 3 is positioned within a certain range from the first plane S1 of the throat 13 to similarly allow the liquid film to extend on the inner wall of the nozzle, thereby enhancing the cooling effect of the liquid film on the throat 13.

[0064] As an optional technical solution of the embodiment of the present application, multiple groups of first spoiler components 2 are arranged at intervals in the regeneration cooling channel 100.

[0065] Moreover, along the length direction of the channel, the distance D between adjacent first spoiler components 2 is c The maximum dimension h of the first bottom spoiler rib 21 in the height direction of the regenerative cooling channel 100 b The ratio between them satisfies the following relationship:

[0066] 10h b ≤Dc≤30h b

[0067] Specifically, the number and spacing of the first spoiler components 2 are determined according to actual conditions, so as to enhance the cooling effect while minimizing the pressure drop loss.

[0068] An embodiment of the present application also discloses a nuclear rocket engine system, including the nozzle structure of any of the above embodiments.

[0069] The embodiments of the present application are described in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only intended to help understand the technical solutions and core concepts of the present application. Therefore, changes or modifications made by those skilled in the art based on the concepts of the present application, the specific implementation methods, and the scope of application of the present application, all fall within the scope of protection of the present application. In summary, the contents of this specification should not be construed as limiting the present application.

Claims

1. A nozzle structure, characterized in that: include: A nozzle body, wherein a plurality of regenerative cooling channels for coolant to pass through are provided between the inner wall and the outer wall of the nozzle body, the nozzle body comprising a first portion, a second portion and a throat connecting the first portion and the second portion, the second portion being used to be connected to a nuclear rocket engine system; a first spoiler assembly, arranged on the first portion and close to the throat, and located in each of the regenerative cooling channels, the first spoiler assembly comprising a first bottom spoiler rib and a first side spoiler rib, the first bottom spoiler rib being arranged on the bottom wall of the regenerative cooling channel, the first side spoiler rib being arranged on the side wall of the regenerative cooling channel, and being distributed on at least one side of the first bottom spoiler rib along the length direction of the regenerative cooling channel; The surface of the first bottom spoiler fin facing the top wall of the regenerative cooling channel is a smooth arc surface, and both ends of the arc surface are smoothly connected to the bottom wall of the regenerative cooling channel; The nozzle structure further includes a second spoiler assembly, which is arranged on the second part and located in each of the regenerative cooling channels, wherein the second spoiler assembly includes a second bottom spoiler rib and a second side spoiler rib, wherein the second bottom spoiler rib is arranged on the bottom wall of the regenerative cooling channel, and the second side spoiler rib is arranged on the side wall of the regenerative cooling channel and is distributed on at least one side of the second bottom spoiler rib along the length direction of the regenerative cooling channel; A cavity is provided between the second bottom spoiler rib and the bottom wall of the regenerative cooling channel, and a through hole is provided on the second bottom spoiler rib, through which the coolant can enter the cavity when flowing along the regenerative cooling channel; the bottom wall of the regenerative cooling channel is configured as a porous structure at a position corresponding to the cavity, so that the coolant in the cavity can penetrate into the nozzle structure through the porous structure.

2. The nozzle structure according to claim 1, characterized in that: The size ratio between the first side spoiler rib and the regeneration cooling channel satisfies the following relationship: <h2 style=";text-align:left;direction:ltr">0.1d<h<h2 style=";text-align:left;direction:ltr"> s <h2 style=";text-align:left;direction:ltr"> <0.2d; Wherein, d is the width of the regenerative cooling channel, h s is the maximum dimension of the first side spoiler rib in the width direction of the regeneration cooling channel.

3. The nozzle structure according to claim 1, characterized in that: The size ratio between the first bottom spoiler fin and the regeneration cooling channel satisfies the following relationship: 0.05h<h b <0.1h; Wherein, h is the height of the regenerative cooling channel, h b is the maximum dimension of the first bottom spoiler rib in the height direction of the regeneration cooling channel.

4. The nozzle structure according to claim 1, characterized in that: The shape and size of the second spoiler component are the same as those of the first spoiler component.

5. The nozzle structure according to claim 1, characterized in that: The throat has a first plane, and the first plane is a cross section corresponding to the position where the inner diameter of the throat is the smallest; The first portion has a second plane and a third plane parallel to the first plane, the distance between the second plane and the first plane is 20 mm, the distance between the third plane and the first plane is 50 mm, and the first spoiler component is located between the second plane and the third plane; The second portion has a fourth plane and a fifth plane parallel to the first plane, the distance between the fourth plane and the first plane is 50 mm, the distance between the fifth plane and the first plane is 100 mm, and the second spoiler component is located within the fourth plane and the fifth plane.

6. The nozzle structure according to claim 1, characterized in that: The porous structure is made of ceramic.

7. The nozzle structure according to claim 1, characterized in that: A plurality of first spoiler components are arranged in intervals in the regeneration cooling channel.

8. A nuclear rocket engine system, characterized in that: The nozzle structure comprises the nozzle structure described in any one of claims 1 to 7.

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