Buffer tank and rocket engine delivery system

Abstract

The application relates to the aerospace technology field, in particular to a buffer tank and a rocket engine delivery system. The buffer tank comprises a tank body and a turbine assembly. The turbine assembly is arranged in the tank body and divides the tank body into a gas cushion cavity close to a sealing end and a compression cavity close to an opening end which are in communication with each other. The turbine assembly comprises a rotating shaft and a plurality of blades arranged on the rotating shaft and capable of rotating around the rotating shaft. A pressure reduction channel is formed between adjacent blades. The buffer tank is installed in a rocket engine liquid delivery system. When a pressure impact occurs and a pressure peak surface is transmitted to the buffer tank, the gas in the buffer tank is compressed, the liquid flows through the turbine assembly, the rotating shaft and the blades are rotated, and the flow resistance of the liquid flowing into the tank body from the opening end is increased. When the pressure impact ends and a pressure loss occurs, the gas in the buffer tank expands and reversely pushes the blades, the pressure is increased, and the pressure impact and the pressure loss are converted into each other.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a buffer tank and a rocket engine delivery system. BACKGROUND

[0002] In the rocket engine delivery system, pressure pulsation and water hammer impact of the on-off valve are very common, and the buffer tank needs to be used to eliminate or weaken the pressure impact. The buffer tank can store and release energy by converting the pulsation and impact energy in the liquid delivery system into other energy, such as elastic potential energy or gas internal energy, so as to weaken or eliminate the pressure impact to a certain extent and ensure the reliable work of the system.

[0003] The common buffer tank of the rocket engine system generally adopts an air-filled buffer tank, which can be divided into a gas-liquid direct contact type, a piston type and a diaphragm type according to the structural form. The gas-liquid direct contact type buffer tank is widely used due to its simple structure and high reliability. However, the gas-liquid direct contact type buffer tank has unadjustable flow resistance, so its response time is unadjustable. If the response time is reduced, a large system pressure overshoot will be caused; if the response time is increased, the system recovery time will be prolonged.

[0004] Therefore, there is an urgent need for a buffer tank and a rocket engine delivery system to solve the technical problems existing in the prior art to a certain extent. SUMMARY

[0005] The purpose of the present application is to provide a buffer tank and a rocket engine delivery system to solve the technical problem of unadjustable flow resistance of the buffer tank in the prior art to a certain extent.

[0006] The present application provides a buffer tank applied to a rocket engine delivery system in which liquid pressure peaks are generated due to liquid pressure impact; the buffer tank comprises a tank body and a turbine assembly:

[0007] One end of the tank body is an open end and the other end is a sealed end; the turbine assembly is arranged in the tank body, and the turbine assembly divides the tank body into a gas cushion cavity close to the sealed end and a compression cavity close to the open end which are in communication with each other;

[0008] The turbine assembly comprises a rotating shaft and a plurality of blades arranged on the rotating shaft and capable of rotating around the rotating shaft; a pressure reduction channel is formed between adjacent blades;

[0009] When the liquid pressure impact occurs, the liquid enters the compression cavity through the open end, pushes the blades to rotate and is introduced into the gas cushion cavity through the pressure reduction channel to increase the flow resistance of the liquid at the open end;

[0010] When a pressure surge occurs, the liquid can compress the gas in the tank body to the air cushion cavity; when the pressure surge ends, the expansion of the gas in the compression cavity pushes the blades to rotate and return from the air cushion cavity to the compression cavity to make up for the pressure loss.

[0011] In the above technical solution, further, an included angle between a tangent line of one end of the blade towards the open end and close to the root of the rotating shaft and an axis of the rotating shaft is set between 6°-8°; an included angle between a tangent line of one side of the blade towards the open end and away from the end of the rotating shaft and the axis of the rotating shaft is set between 2°-5°.

[0012] An included angle between a tangent line of one side of the blade towards the sealed end and close to the root of the rotating shaft and the axis of the rotating shaft is set between 4°-7°; an included angle between a tangent line of one side of the blade towards the sealed end and away from the end of the rotating shaft and the axis of the rotating shaft is set between 4°-8°.

[0013] In the above technical solution, further, the wrap angle of the blade is set between 9°-11°.

[0014] In the above technical solution, further, the wrap angle of the blade is set between 9°-11°, and the thickness of the blade is set between 1mm-5mm.

[0015] In the above technical solution, further, a diameter of a blade surface composed of the plurality of blades is r; a diameter of the tank body is R; a difference between r and R is set between .

[0016] In the above technical solution, further, the tank body comprises a tank body and a tank top cover;

[0017] One of a rim of the tank body towards the tank top cover and a rim of the tank top cover towards the tank body is provided with a groove, and the other is provided with a limiting protrusion;

[0018] The limiting protrusion is matched with the groove for connecting the tank body and the tank top cover.

[0019] In the above technical solution, further, the turbine assembly further comprises a turbine shaft;

[0020] The turbine shaft is sleeved on the rotating shaft, and the plurality of blades are arranged at intervals on the turbine shaft.

[0021] In the above technical solution, further, the turbine assembly further comprises a bearing; the bearing is arranged between the turbine shaft and the rotating shaft.

[0022] Further, the turbine assembly further comprises a blocking ring.

[0023] The blocking ring is sleeved on the end of the turbine shaft away from the top cover of the tank body, and can be used to prevent the bearing from falling off the turbine shaft.

[0024] The application also provides a rocket engine delivery system comprising the buffer tank.

[0025] Compared with the prior art, the application has the following beneficial effects:

[0026] The application provides a buffer tank, which is applied to a rocket engine delivery system that generates a liquid pressure peak surface due to liquid pressure impact.

[0027] One end of the tank body is an open end and the other end is a sealed end; the turbine assembly is arranged in the tank body, and the turbine assembly divides the tank body into a gas cushion cavity near the sealed end and a compression cavity near the open end, which are in communication with each other;

[0028] The turbine assembly comprises a rotating shaft and a plurality of blades arranged on the rotating shaft and capable of rotating around the rotating shaft; a pressure reduction channel is formed between adjacent blades;

[0029] When the liquid pressure impact occurs, the liquid enters the compression cavity through the open end, pushes the blades to rotate and is guided into the gas cushion cavity through the pressure reduction channel to increase the flow resistance of the liquid at the open end;

[0030] When the pressure impact occurs, the liquid can compress the gas in the tank body into the gas cushion cavity; when the pressure impact ends, the gas in the compression cavity expands to push the blades to rotate and return from the gas cushion cavity to the compression cavity to compensate for the pressure loss.

[0031] Specifically, the buffer tank with the above structure is installed in a rocket engine liquid delivery system; when there is pressure pulsation or water hammer impact generated by an on-off valve in the delivery system, a pressure peak surface is generated and transmitted in the delivery system; when the pressure peak surface is transmitted to the buffer tank, the gas in the buffer tank is compressed, the liquid flows through the turbine assembly, the turbine shaft and the blades are rotated, the pressure energy is converted into kinetic energy of the turbine shaft and the blades, the fluid pressure drop is significantly increased, and the flow resistance of the liquid flowing into the tank body through the open end is increased.

[0032] Further, because the pressure impact time is short, the blade will continue to rotate under the action of inertia without the effect of external braking. When the pressure impact ends and pressure loss occurs, the gas in the buffer tank expands and reversely pushes the blade. At this time, the rotation of the blade under the action of inertia is equivalent to a compressor, which can increase the pressure. This can realize the mutual conversion of pressure impact and pressure loss, improve the energy utilization rate, and further optimize the efficiency of the system.

[0033] The application also provides a rocket engine delivery system comprising the above-mentioned buffer tank, and thus has all the beneficial effects of the buffer tank, which will not be described in detail here. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed 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 other drawings can also be obtained by those skilled in the art without creative labor.

[0035] Figure 1 Structure schematic diagram of the buffer tank provided for Embodiment One of the present application;

[0036] Figure 2 Cross-sectional view of the buffer tank provided for Embodiment One of the present application;

[0037] Figure 3 Structure schematic diagram of the turbine assembly in the buffer tank provided for Embodiment One of the present application in a first perspective view;

[0038] Figure 4 Structure schematic diagram of the turbine assembly in the buffer tank provided for Embodiment One of the present application in a second perspective view;

[0039] Figure 5 Structure schematic diagram of the tank body top cover in the buffer tank provided for Embodiment One of the present application;

[0040] Figure 6 Structure schematic diagram of the tank body body in the buffer tank provided for Embodiment One of the present application.

[0041] Reference signs:

[0042] 1-tank body; 2-turbine assembly; 3-open end; 4-sealing end; 5-air cushion cavity; 6-compression cavity; 7-rotary shaft; 8-blade; 9-pressure reduction channel; 10-tank body body; 11-tank body top cover; 12-turbine shaft; 13-bearing; 14-retaining ring; 15-clamp; 16-limiting protrusion; 17-groove; 18-limiting groove. DETAILED DESCRIPTION

[0043] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments.

[0044] The components of the embodiments of the present application generally described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but merely represents selected embodiments of the present application.

[0045] Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present application.

[0046] In the description of the present application, it should be noted that the orientations or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0047] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0048] Embodiment one

[0049] The following refers to Figures 1 to 6 The buffer tank provided in the embodiment is described.

[0050] In this embodiment, a buffer tank is provided, which is applied to a rocket engine delivery system that generates a liquid pressure peak surface due to liquid pressure impact; specifically, the buffer tank comprises a tank body 1 and a turbine assembly 2: one end of the tank body 1 is an open end 3 and the other end is a sealed end 4; the turbine assembly 2 is arranged in the tank body 1, and the turbine assembly 2 divides the tank body 1 into a gas cushion cavity 5 near the sealed end 4 and a compression cavity 6 near the open end 3, which are in communication with each other;

[0051] More specifically, the tank body 1 comprises a tank body 10 and a tank top cover 11; in combination Figure 6 As shown, the tank body 10 is provided with a limiting protrusion 16 towards the edge of the tank top cover 11; in combination Figure 3 As shown, the tank top cover 11 has a groove 17 towards the edge of the tank body 10, the limiting protrusion 16 and the groove 17 are in a matching relationship, the tank body 10 and the tank top cover 11 are connected together through the limiting protrusion 16 and the groove 17, and in actual use, after the tank body 10 and the tank top cover 11 are buckled together, a welding method (welding to the gap formed after the tank body 10 and the tank top cover 11 are connected) is used to further connect the tank body 10 and the tank top cover 11 together.

[0052] Further, the tank body 10 is provided with a clamp 15 corresponding to the outer side wall of the opening end 3, the clamp 15 is used for buffering the installation of the tank, and a wrench can be used to tighten the clamp with the pipeline connector (the pipeline connector here is a pipe connected with the buffer tank in the rocket engine delivery system).

[0053] More specifically, the turbine assembly 2 comprises a rotating shaft 7, a blade 8, a bearing 13, a retaining ring 14 and a turbine shaft 12.

[0054] Further, one end of the rotating shaft 7 is fixed to the inner side wall of the tank top cover 11, and the other end extends towards the compression cavity 6; a limiting groove 18 is formed on the rotating shaft 7 along the circumferential direction thereof.

[0055] Further, the blade 8 is provided with 24 pieces, and the 24 pieces of blades 8 are arranged at intervals on the turbine shaft 12; the turbine shaft 12 is sleeved in the limiting groove 18 through the bearing 13, and the bearing 13 can be positioned in the circumferential direction through the limiting groove 18.

[0056] Further, a thread is formed on the end of the rotating shaft 7 away from the tank top cover 11, and the retaining ring 14 is fixed to the rotating shaft 7 in a threaded connection manner; the retaining ring 14 can be used to position the bearing 13 in the axial direction, preventing the bearing 13 from falling off the rotating shaft 7.

[0057] Preferably, the bearing 13 is in interference fit with the rotating shaft 7 and the turbine shaft 12, respectively.

[0058] Preferably, the blade 8 is integrally formed by 3D printing.

[0059] Specifically, a pressure reduction channel 9 is formed between adjacent blades 8.

[0060] In summary, when the buffer tank with the above-described structure is installed in the rocket engine liquid delivery system, pressure pulsations or water hammer caused by valve switching will generate pressure peaks that are transmitted through the system. When these pressure peaks reach the buffer tank, the gas inside is compressed, and the liquid flows through the turbine assembly 2, causing the turbine shaft 12 and blades 8 to rotate. This increases the flow resistance of the liquid flowing into the tank 1 from the open end 3, causing the turbine shaft and blades to rotate. The pressure energy is converted into the kinetic energy of the rotating turbine shaft and blades, and the fluid pressure drop will increase significantly, which is equivalent to increasing the flow resistance of the liquid flowing into the tank from the open end.

[0061] Furthermore, the above process is essentially equivalent to converting pressure impact into the kinetic energy of turbine rotation and the internal energy of gas. At this time, the system response time is relatively long, which can reduce or even eliminate the overshoot of the system, thus ensuring the structural integrity and operational reliability of the system.

[0062] Furthermore, because the pressure shock time is very short, blade 8 will continue to rotate due to inertia without external braking. When the pressure shock ends and a pressure deficit occurs, the gas in the buffer tank expands and pushes blade 8 in the opposite direction. At this time, blade 8 rotates under inertia, which is equivalent to a compressor, and can increase the pressure. This is equivalent to realizing the mutual conversion between pressure shock and pressure deficit, improving energy utilization and further optimizing the system efficiency.

[0063] It is worth noting that: Combining Figure 4 As shown, the blade surface composed of 24 blades 8 is a single-layer structure. However, the scope of protection in this application is not limited to a single-layer blade surface structure. Depending on the needs and considering quality factors, a multi-layer blade surface structure can be configured (multi-layer blade surfaces are arranged at intervals along the axis of rotation 7), generally recommended to be no more than 3 layers. Additionally, blade surfaces of different diameters can be used, for example, a combination of large and small blades; or, for example, a combination where the blade diameter increases sequentially from the compression chamber 6 to the air cushion chamber 5, which can be understood as an inverted pyramid structure. Furthermore, stronger pressure suppression can be achieved by increasing the number of blades 8.

[0064] In this embodiment, the angle between the tangent of the blade 8 facing the opening end 3 and near the root of the rotating shaft 7 and the axis of the rotating shaft 7 is set between 6° and 8°; preferably, this angle is 7.2°; the angle between the tangent of the blade 8 facing the opening end 3 and away from the rotating shaft 7 and the axis of the rotating shaft 7 is set between 2° and 5°; preferably, this angle is 3.5°.

[0065] The angle between the tangent of the blade 8 on the side facing the sealing end 4 and near the root of the rotating shaft 7 and the axis of the rotating shaft 7 is set between 4° and 7°; preferably, this angle is 5.2°; the angle between the tangent of the blade 8 on the side facing the sealing end 4 and away from the rotating shaft 7 and the axis of the rotating shaft 7 is set between 4° and 8°; preferably, this angle is 10.8°.

[0066] In this embodiment, the wrap angle of the blade 8 is set between 9° and 11°, and the thickness of the blade 8 is set between 1mm and 5mm.

[0067] In this embodiment, the diameter of the blade surface composed of multiple blades 8 is r; the diameter of the tank body 1 is R; then the difference between r and R is set to... During the assembly of the blades 8, a clearance fit is ensured between the blade surface formed by the blades 8 and the side wall of the tank 1, thereby increasing the flow resistance of the inlet liquid. Through the above embodiments, the inlet flow resistance can be significantly increased, by 50-70% compared to a buffer tank without a turbine assembly.

[0068] The above parameters can be understood as follows: inlet hub blade installation angle 7.2°, inlet rim blade installation angle 3.5°, outlet hub blade installation angle 5.6°, outlet rim blade installation angle 5.2°, blade wrap angle 10.8°, blade thickness 1.3mm, number of blades 24; assembly clearance is 0.5-5mm or 0.5mm-10% of the tank's internal diameter.

[0069] Example 2

[0070] This application also provides a rocket engine delivery system including the aforementioned buffer tank, and thus possesses all the beneficial effects of a buffer tank, which will not be elaborated upon here.

[0071] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A buffer tank, used in a rocket engine delivery system where liquid pressure peaks are generated due to liquid pressure surges; characterized in that, The buffer tank includes a tank body and a turbine assembly: One end of the tank is an open end and the other end is a sealed end; the turbine assembly is disposed in the tank, and the turbine assembly divides the tank into an air cushion cavity near the sealed end and a compression cavity near the open end that are connected to each other. The turbine assembly includes a rotating shaft and a plurality of blades disposed on the rotating shaft and capable of rotating about the rotating shaft; a pressure reduction channel is formed between adjacent blades; When liquid pressure impacts, liquid enters the compression chamber through the opening end, drives the blade to rotate, and is guided into the air cushion chamber through the pressure reduction channel to increase the flow resistance of the liquid at the opening end; During a pressure shock, the liquid can compress the gas inside the tank into the air cushion cavity; When the pressure shock ends, the blades rotate under inertia, which acts like a compressor, increasing the pressure to compensate for the pressure loss.

2. The buffer tank according to claim 1, characterized in that, The angle between the tangent of the blade at one end facing the opening and near the root of the rotating shaft and the axis of the rotating shaft is set between 6° and 8°; the angle between the tangent of the blade at one end facing the opening and away from the rotating shaft and the axis of the rotating shaft is set between 2° and 5°. The angle between the tangent of the blade on the side facing the sealing end and near the root of the rotating shaft and the axis of the rotating shaft is set between 4° and 7°; the angle between the tangent of the blade on the side facing the sealing end and away from the rotating shaft and the axis of the rotating shaft is set between 4° and 8°.

3. The buffer tank according to claim 1, characterized in that, The blade wrap angle is set between 9° and 11°.

4. The buffer tank according to claim 1, characterized in that, The blade thickness is set between 1mm and 5mm.

5. The buffer tank according to claim 1, characterized in that, The diameter of the blade surface formed by the multiple blades is r; the diameter of the can body is R; then the difference between r and R is set at 0.1 mm - between.

6. The buffer tank according to claim 1, characterized in that, The tank body includes a tank body and a tank top cover; The tank body has a groove on one of the edges facing the tank top cover and the tank top cover has a limit protrusion on the other. The limiting protrusion is adapted to the groove for connecting the tank body and the tank top cover.

7. The buffer tank according to claim 6, characterized in that, The turbine assembly also includes a turbine shaft; The turbine shaft is sleeved on the rotating shaft, and multiple blades are arranged at intervals on the turbine shaft.

8. The buffer tank according to claim 7, characterized in that, The turbine assembly also includes a bearing; the bearing is disposed between the turbine shaft and the rotating shaft.

9. The buffer tank according to claim 8, characterized in that, The turbine assembly also includes a retaining ring; The retaining ring is fitted onto the end of the turbine shaft away from the top cover of the tank, and can be used to prevent the bearing from falling off the turbine shaft.

10. A rocket engine delivery system, characterized in that, Includes the buffer tank as described in any one of claims 1-9.

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