Efficient energy dissipation device of storage tank for carrier rocket

Abstract

The utility model relates to the field of rocket storage tank pressurization, in particular to a carrier rocket storage tank efficient energy dissipation device which comprises an expansion barrel section, a front bottom cover, a rear bottom cover, an outer layer barrel screen, an inner layer barrel screen, a flow guide cone and a bowl-shaped screen. The edge of the large end of the expansion cylinder section is butted and fixed with the edge of the airflow through hole of the front bottom cover; the edge of the bowl-shaped sieve is in butt joint and fixed with the inner wall of the expansion barrel section, and the protruding side of the bowl-shaped sieve faces the side of the front bottom cover; the bottom end of the diversion cone is fixed with the upper surface of the rear bottom cover; the outer-layer drum screen is arranged outside the inner-layer drum screen in a sleeving mode, the lower edge of the outer-layer drum screen and the lower edge of the inner-layer drum screen are both fixed to the upper surface of the rear bottom cover, the flow guide cone is located in the inner-layer drum screen, the upper edge of the outer-layer drum screen and the upper edge of the inner-layer drum screen are both fixed to the lower surface of the front bottom cover, and the bowl-shaped screen is located in the inner-layer drum screen. The energy dissipation effect of the energy dissipation device can be improved, and the cost of the energy dissipation device is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of rocket tank pressurization, in particular to a high-efficiency energy dissipation device for a tank of a launch vehicle. BACKGROUND

[0002] The pressurization system is an important system to meet the needs of normal operation and structural load of the engine. The function and role of the energy dissipation device located at the top of the tank is to reduce the force and heat impact of the pressurization gas on the tank wall and liquid surface while achieving reasonable energy distribution.

[0003] However, the existing energy dissipation device is often a general configuration, which needs to be specially customized for the pressurization gas and flow in a specific use environment, so that the pressurization gas uniformly enters the tank and smoothly transitions after passing through the energy dissipation device, and finally the pressurization gas tends to be parallel to the axis direction of the tank, thereby reducing the kinetic energy of the pressurization gas entering the tank, so that the pressurization gas cannot directly blow onto the liquid surface to cause liquid splashing, and the energy dissipation device meets the indicators of the pressurization delivery system.

[0004] The energy dissipation device with publication number CN215884126U adopts a multi-layer cylinder screen, and the radial size of the energy dissipation device is large. After the gas flow is blown out, it is very close to the side wall of the tank, resulting in strong impact and heat exchange of the gas flow on the surface of the tank. The pressurization gas cannot be uniformly distributed, which easily causes liquid splashing, and the energy dissipation effect is poor, and also has the problems of large volume and high cost. The cylinder screen spacing of the energy dissipation device with publication number CN115992778A is large, and also has the problem that the gas flow is very close to the side wall of the tank. Moreover, the gas flow changes from axial to radial without using a flow guide device for transition, which easily causes gas flow collision and generates large vortexes, affecting the smooth pressurization of the gas flow, thereby causing the pressurization gas to be unable to be uniformly distributed, easily causing liquid splashing, and the energy dissipation effect is poor, and also has the problems of large volume and high cost.

[0005] Therefore, how to improve the energy dissipation effect of the energy dissipation device and reduce the cost of the energy dissipation device is a technical problem that needs to be solved by the technical personnel in the field at present. Practical new type content

[0006] The present application provides a high-efficiency energy dissipation device for a tank of a launch vehicle to improve the energy dissipation effect of the energy dissipation device and reduce the cost of the energy dissipation device.

[0007] To solve the above technical problems, the present application provides the following technical solutions:

[0008] The application discloses a high-efficiency energy dissipation device for a storage tank of a carrier rocket, which comprises an expansion cylinder section, a front bottom cover, a rear bottom cover, an outer-layer cylinder screen, an inner-layer cylinder screen, a flow guide cone and a bowl screen.

[0009] Preferably, the expansion cylinder section and the front bottom cover are combined to form an integrated structure.

[0010] Preferably, the top end of the flow guide cone is a convex circular arc surface.

[0011] Preferably, the conical surface of the flow guide cone is gradually inclined inward from the top to the middle part, and the conical surface of the flow guide cone is gradually inclined inward from the bottom to the middle part, so that the middle part of the conical surface of the flow guide cone is concave inward.

[0012] Preferably, the edge of the bowl screen is fixed to the inner wall of the expansion cylinder section by welding.

[0013] Preferably, the bottom end of the flow guide cone is fixed to the upper surface of the rear bottom cover by welding.

[0014] Preferably, the lower edge of the outer-layer cylinder screen and the lower edge of the inner-layer cylinder screen are fixed to the upper surface of the rear bottom cover by welding, and the upper edge of the outer-layer cylinder screen and the upper edge of the inner-layer cylinder screen are fixed to the lower surface of the front bottom cover by welding.

[0015] Preferably, the bowl screen has a plurality of bowl screen holes, and all the bowl screen holes are uniformly distributed.

[0016] The high-efficiency energy dissipation device for a storage tank of a carrier rocket as described above, preferably, the outer layer cylinder screen has a plurality of outer layer cylinder screen holes, and all the outer layer cylinder screen holes are uniformly distributed; the inner layer cylinder screen has a plurality of inner layer cylinder screen holes, and all the inner layer cylinder screen holes are uniformly distributed.

[0017] The high-efficiency energy dissipation device for a storage tank of a carrier rocket as described above, preferably, the outer layer cylinder screen holes and the inner layer cylinder screen holes are staggered at a certain angle.

[0018] In view of the above background, the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application adopts a structure of a bowl screen combined with a double-layer cylinder screen, and has fewer cylinder screens arranged in the radial direction compared with the prior art, thereby not only reducing the occupation of the space of the storage tank, but also playing a good role in weakening the impact and heat exchange of the pressurized gas flow on the wall surface of the storage tank.

[0019] In addition, the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application adopts a bowl screen combined with a flow guide cone to dissipate the energy of the pressurized gas flow and effectively guide the direction of the pressurized gas flow, thereby inhibiting the generation of large vortexes and making the pressurized gas flow change direction more smoothly and stably in the energy dissipation device and flow to the double-layer cylinder screen, so as to realize the control of the outflow direction of the pressurized gas flow.

[0020] In addition, the porous honeycomb structure of the double-layer cylinder screen can make the pressurized gas flow blow out uniformly and horizontally, effectively avoiding the pressurized gas flow from directly impacting the liquid surface of the rocket propellant in the storage tank, and playing a good role in stabilizing the liquid surface and the pressure of the rocket propellant. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or prior art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0022] Figure 1 is a schematic diagram of the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application;

[0023] Figure 2 is a sectional view of the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application;

[0024] Figure 3 is a schematic diagram of the bowl screen of the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application;

[0025] Figure 4 is a schematic diagram of the flow guide cone of the high-efficiency energy dissipation device for a storage tank of a carrier rocket provided by the present application. DETAILED DESCRIPTION

[0026] Embodiments of the present application are described below in detail, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. In addition, spatially relative terms such as "upper", "lower", "left", "right", "front", "back", and the like are used for convenience in describing the position relationship between two components, and are not to be construed as limiting the present application.

[0027] As shown in Figure 1 and Figure 2 The present application provides an efficient energy dissipation device for a storage tank of a launch vehicle, comprising: an expansion cylinder segment 110, a front bottom cover 120, a rear bottom cover 130, an outer layer cylinder screen 140, an inner layer cylinder screen 150, a flow guide cone 160, and a bowl screen 170.

[0028] The expansion cylinder segment 110 has a gas flow passage through both ends, and the front bottom cover 120 has a gas flow hole through both ends. The small end of the expansion cylinder segment 110 is used to communicate with the pipeline of the pressurization system, and the edge of the large end of the expansion cylinder segment 110 is butt-jointed and fixed with the edge of the gas flow hole of the front bottom cover 120, so as to combine the expansion cylinder segment 110 and the front bottom cover 120 to form an integral whole. Optionally, the integral whole formed by the combination of the expansion cylinder segment 110 and the front bottom cover 120 is an integrally formed structure, thereby facilitating the mechanical properties of the integrally formed structure.

[0029] As shown in Figure 3 The bowl screen 170 has a bowl screen hole 171 through the inside and outside, the edge of the bowl screen 170 is butt-jointed and fixed with the inner wall of the expansion cylinder segment 110, and the convex side of the bowl screen 170 faces the side of the front bottom cover 120. Optionally, the bottom of the convex side of the bowl screen 170 protrudes out of the gas flow hole of the front bottom cover 120. Further optionally, the edge of the bowl screen 170 is fixed with the inner wall of the expansion cylinder segment 110 by welding. Yet optionally, the edge of the bowl screen 170 is butt-jointed to the same circumference of the inner wall of the expansion cylinder segment 110. Still optionally, the bowl screen 170 has a plurality of bowl screen holes 171, and all the bowl screen holes 171 are uniformly distributed.

[0030] As shown in Figure 4 The flow guide cone 160 is conical, the top end of which extends upward, and the bottom end of which is fixed with the upper surface of the rear bottom cover 120. Optionally, the top end of the flow guide cone 160 is a convex arc surface upward, so that the flow guide cone 160 is streamlined. Further optionally, the conical surface of the flow guide cone 160 gradually inclines inward from the top to the middle part, and the conical surface of the flow guide cone 160 gradually inclines inward from the bottom to the middle part, so that the middle part of the conical surface of the flow guide cone 160 is concave inward. Yet optionally, the bottom end of the flow guide cone 160 is fixed with the upper surface of the rear bottom cover 120 by welding.

[0031] The outer layer cylinder screen 140 and the inner layer cylinder screen 150 are both in the shape of a cylinder penetrating from top to bottom, the outer layer cylinder screen 140 has outer layer cylinder screen holes 141 penetrating from the inside to the outside, the inner layer cylinder screen 150 has inner layer cylinder screen holes 151 penetrating from the inside to the outside, and the outer layer cylinder screen 140 is sleeved to the outside of the inner layer cylinder screen 150; the lower edge of the outer layer cylinder screen 140 and the lower edge of the inner layer cylinder screen 150 are both fixed to the upper surface of the rear bottom cover 130, and the flow guide cone 160 is located in the inside of the inner layer cylinder screen 150; the upper edge of the outer layer cylinder screen 140 and the upper edge of the inner layer cylinder screen 150 are both fixed to the lower surface of the front bottom cover 120, and the bowl-shaped screen 170 is located in the inside of the inner layer cylinder screen 150.

[0032] Optionally, the lower edge of the outer layer cylinder screen 140 and the lower edge of the inner layer cylinder screen 150 are fixed to the upper surface of the rear bottom cover 130 by welding; the upper edge of the outer layer cylinder screen 140 and the upper edge of the inner layer cylinder screen 150 are both fixed to the lower surface of the front bottom cover 120 by welding. Further optionally, the outer layer cylinder screen 140 has a plurality of outer layer cylinder screen holes 141, and all the outer layer cylinder screen holes 141 are uniformly distributed; the inner layer cylinder screen 150 has a plurality of inner layer cylinder screen holes 151, and all the inner layer cylinder screen holes 151 are uniformly distributed. Yet further optionally, the outer layer cylinder screen holes 141 are staggered at a certain angle with the inner layer cylinder screen holes 151, that is, the outer layer cylinder screen holes 141 do not correspond to the inner layer cylinder screen holes 151, thereby being conducive to the smooth and stable airflow.

[0033] When the high-efficiency energy dissipation device for the tank of a carrier rocket is used, the pressurized airflow enters the inner layer cylinder screen 150 through the expansion cylinder section 110 and the bowl-shaped screen 170, and then the energy of the pressurized airflow is weakened through the flow guide cone 160, the inner layer cylinder screen 150 and the outer layer cylinder screen 140, and enters the tank.

[0034] The high-efficiency energy dissipation device for the tank of a carrier rocket of the present application adopts the structure of the bowl-shaped screen 170 combined with the double-layer cylinder screen (the outer layer cylinder screen 140 and the inner layer cylinder screen 150), and the number of the cylinder screens arranged in the radial direction is less than that of the prior art, which not only reduces the occupation of the space of the tank, but also plays a good role in weakening the impact and heat exchange of the pressurized airflow on the wall surface of the tank.

[0035] In addition, the high-efficiency energy dissipation device for the tank of a carrier rocket of the present application adopts the way of the bowl-shaped screen 170 combined with the flow guide cone 160 to dissipate the energy of the pressurized airflow, and effectively guide the direction of the pressurized airflow, inhibit the generation of large vortexes, make the pressurized airflow more smoothly and stably change direction in the inside of the energy dissipation device to flow to the double-layer cylinder screen, and realize the control of the outflow direction of the pressurized airflow.

[0036] In addition, the porous honeycomb structure of the double-layer cylinder screen can make the pressurized airflow blow out uniformly and horizontally, effectively avoid the pressurized airflow from directly impacting the liquid surface of the rocket propellant in the tank, and play a good role in the stability of the liquid surface of the rocket propellant and the stability of the pressure.

[0037] It will be apparent to those skilled in the art that the application is not limited to the details of the foregoing embodiment, that the application can be implemented in other specific forms without departing from the spirit or essential character thereof, and that the intention is to be considered as limited solely by the terms of the appended claims, and not by the foregoing description, which should be interpreted merely as exemplary and non-limiting. All changes coming within the meaning and equivalency range of the claims are intended to be embraced therein. No reference signs in the claims should be considered as limiting the scope of the claims to the identity of the reference signs themselves.

[0038] Furthermore, it should be understood that although the description is made on the basis of the embodiments, not every embodiment contains only one independent technical solution, and the description is made in this way only for the sake of clarity, and those skilled in the art should consider the description as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that those skilled in the art can understand.

Claims

1. A high-efficiency energy dissipation device for a launch vehicle tank, characterized by comprising: The application relates to a cylinder screen, which comprises the following parts: an expansion cylinder segment, a front bottom cover, a rear bottom cover, an outer-layer cylinder screen, an inner-layer cylinder screen, a flow guide cone and a bowl screen; the expansion cylinder segment is provided with airflow passages penetrating through two ends, the front bottom cover is provided with airflow holes penetrating through two ends, and the edge of the large end of the expansion cylinder segment is fixedly connected with the edge of the airflow hole of the front bottom cover; the bowl screen is provided with bowl screen holes penetrating through the inside and outside, the edge of the bowl screen is fixedly connected with the inner wall of the expansion cylinder segment, and the convex side of the bowl screen faces the front bottom cover side; the flow guide cone is in a conical shape, the top end of the flow guide cone extends upwards, and the bottom end of the flow guide cone is fixed with the upper surface of the rear bottom cover; the outer-layer cylinder screen and the inner-layer cylinder screen are both in a cylinder shape penetrating through the top and bottom, the outer-layer cylinder screen is provided with outer-layer cylinder screen holes penetrating through the inside and outside, the inner-layer cylinder screen is provided with inner-layer cylinder screen holes penetrating through the inside and outside, and the outer-layer cylinder screen is sleeved to the outside of the inner-layer cylinder screen; the lower edge of the outer-layer cylinder screen and the lower edge of the inner-layer cylinder screen are both fixed with the upper surface of the rear bottom cover, the flow guide cone is located in the inside of the inner-layer cylinder screen, the upper edge of the outer-layer cylinder screen and the upper edge of the inner-layer cylinder screen are both fixed with the lower surface of the front bottom cover, and the bowl screen is located in the inside of the inner-layer cylinder screen.

2. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1, characterized by, The whole formed by the combination of the expansion cylinder segment and the front bottom cover is an integrally-formed structure.

3. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The top end of the flow guide cone is a convex circular arc surface.

4. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 3, characterized by, The conical surface of the flow guide cone gradually inclines inward from the top to the middle part, and the conical surface of the flow guide cone gradually inclines inward from the bottom to the middle part, so that the middle part of the conical surface of the flow guide cone is concave inward.

5. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The edge of the bowl screen is fixed with the inner wall of the expansion cylinder segment through welding.

6. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The bottom end of the flow guide cone is fixed with the upper surface of the rear bottom cover through welding.

7. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The lower edge of the outer-layer cylinder screen and the lower edge of the inner-layer cylinder screen are fixed with the upper surface of the rear bottom cover through welding. The upper edge of the outer-layer cylinder screen and the upper edge of the inner-layer cylinder screen are both fixed with the lower surface of the front bottom cover through welding.

8. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The bowl screen is provided with a plurality of bowl screen holes, and all the bowl screen holes are uniformly distributed.

9. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 1 or 2, characterized by, The outer-layer cylinder screen is provided with a plurality of outer-layer cylinder screen holes, and all the outer-layer cylinder screen holes are uniformly distributed. The inner-layer cylinder screen is provided with a plurality of inner-layer cylinder screen holes, and all the inner-layer cylinder screen holes are uniformly distributed.

10. The high-efficiency energy dissipation device for a tank of a launch vehicle according to claim 9, characterized by, The outer-layer cylinder screen holes and the inner-layer cylinder screen holes are staggered at a certain angle.

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