CN111803979B

CN111803979B - Low-temperature propellant discharge treatment device

Info

Publication number: CN111803979B
Application number: CN202010925555.2A
Authority: CN
Inventors: 罗天培; 孔凡超; 张家仙; 王相成; 周芳; 刘瑞敏; 喻闯闯; 吴薇梵; 张佳; 魏仁敏; 李茂�
Original assignee: Beijing Institute of Aerospace Testing Technology
Current assignee: Beijing Institute of Aerospace Testing Technology
Priority date: 2020-09-07
Filing date: 2020-09-07
Publication date: 2021-03-09
Anticipated expiration: 2040-09-07
Also published as: CN111803979A

Abstract

The invention relates to the technical field of fluid emergency discharge, in particular to a low-temperature propellant discharge treatment device, which comprises: a collecting structure having an opening disposed in correspondence with the fluid outlet of the discharge pipe; and the heat exchange plate is arranged on the outer wall of the collecting structure. The invention provides a low-temperature propellant discharge treatment device which is high in evaporation speed, short in existing time and small in potential safety hazard.

Description

Low-temperature propellant discharge treatment device

Technical Field

The invention relates to the technical field of fluid emergency discharge, in particular to a low-temperature propellant discharge treatment device.

Background

At present, the carrier rocket adopting chemical propulsion is still the first choice for people to enter and exit space, wherein the low-temperature propellant is an important branch of the chemical propellant, the low-temperature propellant is non-toxic and pollution-free, and the advantages of the low-temperature propellant in comparison with the conventional propellant are incomparable. When the united states rockschid-martin company evaluates the united states re-moon program, comparative analysis of the scheme of using conventional propellants and low-temperature propellants shows that the scale of the system can be significantly reduced by using low-temperature propellants, the weight of the system can be reduced by nearly 45%, and the cost of single emission can be reduced by about 10 billion yuan.

Meanwhile, the low-temperature propellant has the characteristics of low boiling point, easiness in leakage and diffusion and the like, and brings great challenges to large-scale application. The existing discharge methods of the low-temperature liquid propellant comprise three types of high-altitude discharge, combustion pool discharge and cofferdam discharge, wherein the high-altitude discharge method is only suitable for the discharge of the low-temperature propellant with small flow, the discharged steam sinks due to low temperature after the flow is increased, and the risk of explosion is extremely high after an explosive mixture formed by mixing the steam with air approaches the ground; the discharge flow range of the combustion pool discharge method is not wide, and the deflagration risk also exists when the large flow is required to be rapidly discharged in an emergency; the cofferdam discharge is suitable for large-flow emergency discharge, the form of an earth dike or a concrete dike is generally adopted at present, the low-temperature propellant can volatilize into gas due to low boiling point, but the evaporation speed of the low-temperature propellant in the cofferdam is slow, namely the existence time of a hazard source in the cofferdam is long, and the potential safety hazard is large.

Disclosure of Invention

Therefore, the invention aims to overcome the defects of slow evaporation speed, long existence time and potential safety hazard in the process of discharging fluids such as low-temperature propellants and the like in the prior art, and provides a low-temperature propellant discharge treatment device with fast evaporation speed, short existence time and small potential safety hazard.

In order to solve the above technical problem, the present invention provides a low temperature propellant discharge treatment apparatus, comprising:

a collecting structure having an opening disposed in correspondence with the fluid outlet of the discharge pipe;

and the heat exchange plate is arranged on the outer wall of the collecting structure.

The low-temperature propellant discharging and treating device is characterized in that a plurality of heat exchange plates are arranged on the outer wall of the collecting structure at equal intervals.

The low-temperature propellant discharge treatment device is characterized in that the heat exchange plate is parallel to the axial direction of the collection structure and extends from the top end to the bottom end of the outer wall of the collection structure.

The low-temperature propellant discharging and treating device is characterized in that the collecting structure and the heat exchange plate are made of aluminum alloy.

The low-temperature propellant discharge treatment device is characterized in that a heating plate is further arranged at the bottom of the collecting structure.

The low-temperature propellant discharge treatment device is characterized in that the collecting structure is a cylinder.

The low-temperature propellant discharge treatment device is characterized in that the height of the cylinder is equal to the diameter of the bottom surface of the cylinder.

The low-temperature propellant discharge treatment device is characterized in that water is contained in the collecting structure.

The volume of water in the low-temperature propellant discharge treatment device is 1/3 of the volume of the collecting structure.

The technical scheme of the invention has the following advantages:

1. according to the low-temperature propellant discharge processing device provided by the invention, when low-temperature propellant and other fluids need to be discharged in an emergency, the fluids in the discharge pipe directly enter the collection structure through the opening, and the heat exchange plate is arranged on the outer wall of the collection structure and can play a role of a rib, so that the heat exchange area is increased, the thermal resistance of convective heat exchange is reduced, the heat transfer capacity of the device is enhanced, the evaporation speed is increased, a hazard source is rapidly eliminated, and the potential safety hazard is reduced.

2. According to the low-temperature propellant discharge treatment device provided by the invention, the heating plate is arranged at the bottom of the collecting structure, and the heating plate and the heat exchange plate act simultaneously, so that the evaporation speed of fluids such as low-temperature propellant is further increased, and the potential safety hazard is reduced.

3. Compared with the traditional cubic structure, the low-temperature propellant discharge processing device provided by the invention has the advantages that the cylindrical collection structure can effectively reduce the diffusion range of combustible gas clouds after the evaporation of fluids such as low-temperature propellants no matter the wind direction of the atmospheric environment, and is suitable for the discharge requirements in different wind directions, and meanwhile, the collection structure has higher strength and is not easy to damage when the collection structure is contracted due to the contact with the fluids such as the low-temperature propellants.

4. According to the low-temperature propellant discharge treatment device provided by the invention, the collection structure is filled with water, and the water has larger heat capacity and heat conductivity, so that the low-temperature propellant and other fluids are prevented from directly impacting on the bottom surface of the collection structure while the low-temperature propellant and other fluids are ensured to be rapidly evaporated, the temperature stress of the bottom surface of the collection structure is reduced, and the service life of the device is prolonged.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic view of a cryogenic propellant discharge treatment apparatus provided by the present invention.

Description of reference numerals:

1. a collection structure; 2. a heat exchange plate; 3. a discharge pipe; 4. heating plates; 5. and (3) water.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Fig. 1 shows a specific embodiment of a cryogenic propellant discharge treatment device, in this embodiment, a cryogenic propellant for a launch vehicle, such as liquid hydrogen, liquid oxygen, or liquid methane, and this embodiment is applied to a situation where a cryogenic system of a rocket launch site or a test stand fails and requires a large amount of emergency discharge of cryogenic propellant, including a collection structure 1 and a heat exchange plate 2.

The collecting structure 1 is a cylinder with the same height and diameter at the bottom surface, the cylinder is made of aluminum alloy, the top of the collecting structure is provided with an opening which is arranged corresponding to the fluid outlet of the discharge pipe 3, the cross-sectional area of the opening is far larger than that of the fluid outlet of the discharge pipe 3, and the fluid outlet of the discharge pipe 3 extends to the inside of the cylinder through the top opening. The bottom of the cylinder can also be made of stainless steel. The inner diameter of the discharge pipe 3 is determined according to the maximum discharge amount, the flow velocity in the pipe is less than 6m/s, and the volume of the cylinder is 3 times of the maximum discharge amount of the discharge pipe 3.

A plurality of rectangular heat exchange plates 2 are arranged on the outer wall of the collecting structure 1 at equal intervals, and the heat exchange plates 2 and the collecting structure 1 are integrally processed and formed or fixed in a welding or splicing mode and the like. Heat transfer board 2 is the aluminum alloy material, heat transfer board 2 is on a parallel with the axial setting of collecting structure 1, and certainly the outer wall top of collecting structure 1 extends to the bottom to furthest increases heat transfer area for the evaporation rate of low temperature propellant.

In order to further accelerate the evaporation of the low-temperature propellant, a heating plate 4 is arranged at the bottom of the collecting structure 1. The heating plate 4 is a plate body embedded with resistance wires, and the heating plate 4 completely covers the bottom surface of the collecting structure 1.

In order to prevent the low-temperature propellant from directly impacting the bottom surface of the collecting structure 1, water 5 is filled in the collecting structure 1, and the volume of the water 5 is 1/3 of that of the collecting structure 1.

Before the low-temperature propellant in the discharge pipe 3 needs to be discharged, 1/3 volume of water 5 is injected into the cylindrical collecting structure 1, then the heating plate 4 at the bottom is opened, the low-temperature propellant is discharged into the collecting structure 1, the low-temperature propellant exchanges heat with the outer wall of the collecting structure 1 when contacting the outer wall, and further the evaporation rate is improved through the heat exchange plate 2 on the outer wall of the collecting structure 1 and the combined action of the heating plate 4 at the bottom and the water 5; meanwhile, the direct impact of the low-temperature propellant and the bottom surface of the collecting structure 1 is avoided due to the existence of water in the collecting structure 1. And after the low-temperature propellant is completely evaporated, closing the heating plate 4, and finishing the treatment work.

As an alternative embodiment, the heat exchanger plates 2 may be distributed helically along the outer wall of the collecting structure 1, or as annular plates spaced apart in an axial direction perpendicular to the collecting structure 1.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.

Claims

1. A low-temperature propellant discharge processing device is characterized in that the low-temperature propellant liquid hydrogen discharge processing device for a carrier rocket comprises:

the collecting structure (1) is provided with an opening which is arranged corresponding to the fluid outlet of the discharge pipe (3), the cross-sectional area of the opening is far larger than that of the fluid outlet of the discharge pipe (3), the volume of the collecting structure (1) is 3 times of the maximum discharge amount of the discharge pipe (3), the collecting structure (1) is a cylinder, and the height and the bottom surface of the cylinder are equal in diameter;

the heat exchange plate (2) is arranged on the outer wall of the collecting structure (1);

wherein the collecting structure (1) is filled with water (5), and the volume of the water (5) is 1/3 of the volume of the collecting structure (1); the bottom of the collecting structure (1) is also provided with a heating plate (4).

2. Cryogenic propellant discharge treatment device according to claim 1, characterized in that a plurality of heat exchanger plates (2) are arranged at equal intervals on the outer wall of the collecting structure (1).

3. The arrangement according to claim 2, characterized in that the heat exchanger plates (2) are arranged parallel to the axial direction of the collecting structure (1) and extend from the top end to the bottom end of the outer wall of the collecting structure (1).

4. The cryogenic propellant discharge treatment device according to any one of claims 1-3 wherein the collection structure (1) and the heat exchanger plate (2) are both of aluminium alloy.