Siphon outflow device suitable for carrier rocket storage tank
By designing a siphon outflow device with siphon bend pipe, whirlwind blades and storage devices in the liquid carrier rocket tank, the liquid level collapse and vortex problems are solved, the propellant utilization rate is improved, and the engine is ensured to work normally.
Patent Information
- Application Number
- CN202411486078.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-23
- Publication Date
- 2024-12-24
AI Technical Summary
At the end of the outflow of the propellant in the liquid carrier rocket tank, the liquid level collapses and vortexes due to the storage box boundary and outlet factors, which affects the normal operation of the engine. In addition, the traditional outflow device cannot use the propellant at the bottom of the storage box, resulting in low propellant utilization. .
Design a siphon outflow device, including a curved siphon bend, vortex blade and storage device, utilize propellant below the outlet through the siphon effect, and prevent liquid surface collapse through the design of exhaust holes and flow blocking plates and Vortex to improve propellant utilization.
Effectively utilize propellant at the bottom of the storage tank to prevent liquid surface collapse and vortex, improve the utilization rate of propellant, reduce gas inclusion, and ensure the normal operation of the engine.
Smart Images
Figure CN119177902A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the field of liquid carrier rockets, in particular to a siphon outflow device suitable for a carrier rocket tank. Background Art
[0002] At the end of the outflow of the propellant in the tank of a liquid launch vehicle, due to the influence of factors such as the tank boundary, outlet and external interference on the local flow characteristics, liquid surface collapse, vortex and other phenomena will appear above the outlet. The vortex and collapse phenomenon is unique to liquid rockets and occurs at the end of the single-stage combustion of the rocket. If effective suppression measures are not taken, vortex and collapse will cause a large amount of gas to be mixed in the propellant, flow through the delivery pipe to the engine turbo pump, seriously affecting the normal operation of the engine, and even causing cavitation and causing the engine to explode. Therefore, it is an effective way to ensure the normal operation of the launch vehicle power system and improve the carrying capacity of the launch vehicle by designing an appropriate outflow device to prevent or delay the occurrence of vortex and collapse and improve the utilization rate of the propellant in the tank. However, the bottom structure of some existing liquid launch vehicle tanks is relatively complex, and the outlet is located at a high position. Traditional outflow devices such as half cover plates and vortex elimination blades cannot utilize the propellant below the outlet. Therefore, it is necessary to design a new outflow device to solve the problem of utilizing the propellant at the bottom of the tank below the outlet, thereby further improving the utilization rate of the tank propellant. Summary of the invention
[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and provide a siphon outflow device suitable for a launch vehicle tank. For liquid launch vehicles with a relatively complex tank bottom structure and a relatively high outlet position, the siphon outflow device solves the problem of utilizing the propellant at the bottom of the tank below the outlet, while preventing the occurrence of liquid level collapse, vortexes, etc. above the outlet.
[0004] The technical solution of the present invention is: a siphon outflow device suitable for a launch vehicle tank, characterized in that: the siphon outflow device is installed in the launch vehicle tank, includes a siphon bend, vortex-eliminating blades and a retention device, and utilizes the propellant below the outlet through the siphon effect; the siphon bend is a curved tubular structure, one end of which is connected to the outlet of the tank, and the other end is an inlet end, the inlet end is parallel to the horizontal plane and is lower than the outlet; a plurality of vortex-eliminating blades are evenly arranged around the outer wall surface of the inlet end of the siphon bend, the upper side of the vortex-eliminating blades is fixed to the outer wall surface of the inlet end, and the lower side extends to below the inlet end; the retention device is located at the top of the siphon bend, and the bottom of the retention device is connected to the siphon bend through a plurality of exhaust holes.
[0005] Furthermore, the volume of the retention device, the number and diameter of the exhaust holes meet the following conditions: during the outflow of the propellant, the time when the propellant in the retention device flows into the siphon bend through the exhaust holes is later than the time when the propellant liquid level in the tank drops to the height of the inlet end of the siphon bend.
[0006] Furthermore, a baffle is provided inside the siphon bend below the exhaust hole to increase the flow resistance at the exhaust hole and reduce the propellant flow at the exhaust hole.
[0007] Furthermore, the cross section of the spoiler is an arc shape.
[0008] Furthermore, the width of the lower end of the anti-swirl blade is 0.15D, the width of the upper end is 0.3D, the height is 0.6D, and the lower end of the blade is 0.15D lower than the inlet end of the siphon bend; D is the diameter of the siphon bend.
[0009] Furthermore, the spacing angle between each swirl-eliminating blade is 10° to 15°, and the number of blades is greater than 20.
[0010] Furthermore, a local expansion is performed at the inlet end of the siphon elbow, and the cross-sectional area of the pipe opening at the inlet end is 2 to 3 times the cross-sectional area of the siphon elbow pipe.
[0011] Furthermore, the retention device is a cylindrical structure, and the upper end of the cylinder is angled inwardly by 25 to 30 degrees to prevent the propellant in the retention device from shaking out due to lateral overload during the outflow process.
[0012] The advantages of the present invention compared with the prior art are:
[0013] (1) The present invention innovatively proposes a siphon elbow outflow solution in the tank. The siphon elbow is designed as a bent metal pipe, one end of which is connected to the original outlet of the tank, and the other end is the inlet end of the siphon elbow. The inlet end is designed to be lower than the plane of the original outlet. The siphon effect is used to further effectively utilize the propellant below the outlet, solving the problem that the propellant below the outlet of the tank cannot be utilized. Especially for tanks with complex bottom structures, the utilization efficiency of the propellant in the tank is effectively improved.
[0014] (2) The present invention designs a retention solution to solve the problem of air entrapment. Due to the curved structure of the siphon bend, during the propellant filling process, if the gas inside the siphon bend cannot be discharged, air entrapment will occur during the propellant outflow process. Therefore, a small exhaust hole is designed at the high point of the siphon bend. In order to further prevent the gas from entering the siphon bend when the liquid level is lower than the exhaust hole during the outflow process and causing premature air entrapment, a retention device is installed above the small hole. The propellant in the retention device plays a liquid sealing role, which effectively solves the problem that the gas in the siphon bend cannot be discharged during the filling process and the problem of premature air entrapment during the outflow process.
[0015] (3) The present invention proposes a flow blocking scheme based on total pressure suppression. During the outflow of propellant, the size relationship between the retention device and the exhaust hole satisfies that the time when the propellant in the retention device flows out is later than the time when the propellant liquid level in the tank reaches the plane height of the inlet end of the siphon bend, thereby ensuring the liquid sealing effect of the retention device. Furthermore, a baffle is installed inside the siphon bend to increase the flow resistance at the small hole in the retention device and reduce the propellant flow at the small hole, so that the volume of the retention device is reduced by 1 / 3.
[0016] 4) The present invention proposes a scheme of adding anti-vortex blades at the inlet end of the siphon bend. The anti-vortex blades are installed around the outer wall surface at the inlet of the siphon bend. When the liquid level is high, the vortex air entrained in the outflow process can be suppressed from entering the delivery pipe, thereby delaying the time when air entrainment occurs in the delivery pipe and significantly reducing the remaining amount of propellant when air entrainment occurs. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 It is a cross-sectional view of a siphon outflow device in an embodiment of the present invention;
[0018] Figure 2 It is a three-dimensional diagram of the siphon outflow device in an embodiment of the present invention. DETAILED DESCRIPTION
[0019] In order to better understand the technical solution of the present invention, the embodiments of the present invention are described in detail below in conjunction with the accompanying drawings. The parts of each structure in the accompanying drawings will be described separately. It is worth noting that the components not shown in the drawings or not described in words are forms known to ordinary technicians in the relevant technical field.
[0020] like Figure 1 and Figure 2 As shown, the siphon outflow device provided in this embodiment is composed of a siphon bend 1, swirl-eliminating blades 2, and a retention device 3.
[0021] Siphon bend 1, the entire siphon outflow device is installed in the launch vehicle tank. First, the layout of the outflow siphon bend 1 is determined. One end of the siphon bend 1 is connected to the tank outlet through a flange, and the other end is the inlet end of the siphon bend 1. The inlet end is in a flat state, and its horizontal plane is lower than the outlet position.
[0022] Preferably, the pipeline is partially expanded at the inlet end, and the cross-sectional area of the pipe opening at the inlet end is 2 to 3 times the cross-sectional area of the siphon elbow 1 .
[0023] Preferably, the spatial direction of the siphon elbow 1 can be designed according to the specific geometric shape inside the tank.
[0024] The swirl-eliminating blades 2 are evenly arranged around the outer wall surface of the inlet end of the siphon bend 1, and are used to prevent the vortex-entrained air generated during the outflow process from entering the delivery pipe.
[0025] Preferably, if the diameter of the siphon bend 1 is D, the width of the lower end of the vortex-eliminating blade is about 0.15D, the width of the upper end is about 0.3D, the height is about 0.6D, and the lower end of the blade is about 0.15D lower than the inlet end of the siphon pipe; the angle between the vortex-eliminating blades is about 10° to 15°, and the number of blades is more than 20.
[0026] A retention device 3 is provided at the top of the siphon bend 1, and four exhaust holes 4 with a diameter of 1 mm to 3 mm are designed to communicate with the bottom of the retention device 3 and the siphon bend 1 to solve the high-point exhaust problem of the siphon during the filling process and the liquid sealing problem at the end of the outflow; the volume of the retention device 3 and the diameter of the exhaust hole 4 need to meet the requirement that the time when the propellant in the retention device flows out through the exhaust hole 4 is later than the time when the propellant liquid level in the tank drops to the plane height of the inlet end of the siphon bend 1.
[0027] Preferably, the upper end of the retention device is angled at 30° to prevent lateral overload during outflow and the propellant in the retention device from shaking out.
[0028] Preferably, a baffle 5 is arranged inside the siphon bend 1 below the exhaust hole 4. The baffle has an arc-shaped cross section with a radius of 25 mm and a width of 30 mm. It utilizes the local stagnation pressure of the siphon to reduce the liquid flow rate through the exhaust hole in the retention device.
[0029] It is to be understood that the present invention is described by way of embodiments, and it is known to those skilled in the art that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. In addition, under the teachings of the present invention, these features and embodiments may be modified to adapt to specific circumstances without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and embodiments that can fall within the scope of the claims of this application all fall within the scope protected by the present invention.
[0030] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.
Claims
1. A siphon outflow device suitable for a launch vehicle tank, characterized in that: The siphon outflow device is installed in a launch vehicle tank, and comprises a siphon bend (1), swirl-eliminating blades (2) and a retention device (3), and utilizes the propellant below the outlet through the siphon effect; the siphon bend (1) is a bent tubular structure, one end of which is connected to the outlet of the tank, and the other end is an inlet end, the inlet end is parallel to the horizontal plane and is lower than the outlet; a plurality of swirl-eliminating blades (2) are evenly arranged around the outer wall surface of the inlet end of the siphon bend (1), the upper side of the swirl-eliminating blades is fixed to the outer wall surface of the inlet end, and the lower side extends to below the inlet end; the retention device (3) is located at the top of the siphon bend (1), and the bottom of the retention device (3) is connected to the siphon bend (1) through a plurality of exhaust holes (4).
2. The siphon outflow device for a launch vehicle tank according to claim 1, characterized in that: The volume of the storage device (3) and the number and diameter of the exhaust holes (4) satisfy the following condition: during the outflow of the propellant, the time at which the propellant in the storage device (3) flows into the siphon bend (1) through the exhaust holes (4) is completely exceeded by the time at which the propellant liquid level in the tank drops to the height of the inlet end of the siphon bend (1).
3. The siphon outflow device for a launch vehicle tank according to claim 2, characterized in that: A baffle plate (5) is arranged inside the siphon elbow (1) below the exhaust hole to increase the flow resistance at the exhaust hole (4) and reduce the propellant flow at the exhaust hole (4).
4. The siphon outflow device for a launch vehicle tank according to claim 3, characterized in that: The cross section of the spoiler (5) is in the shape of an arc.
5. The siphon outflow device for a launch vehicle tank according to claim 1, characterized in that: The width of the lower end of the anti-swirl blade (2) is 0.15D, the width of the upper end is 0.3D, and the height is 0.6D. The lower end of the blade is 0.15D lower than the inlet end of the siphon bend pipe; D is the diameter of the siphon bend pipe.
6. The siphon outflow device for a launch vehicle tank according to claim 5, characterized in that: The spacing angle between each anti-swirl blade is 10° to 15°, and the number of blades is greater than 20.
7. The siphon outflow device for a launch vehicle tank according to claim 1, characterized in that: The inlet end of the siphon elbow (1) is locally expanded, and the cross-sectional area of the pipe opening at the inlet end is 2 to 3 times the cross-sectional area of the pipe of the siphon elbow (1).
8. The siphon outflow device for a launch vehicle tank according to claim 1, characterized in that: The storage device (3) is a cylindrical structure, and the upper end of the cylinder is inwardly formed with a 25-30 degree angle, so as to prevent the propellant in the storage device from shaking out due to lateral overload during the outflow process.