CN112922745B

CN112922745B - Contrary rotation type sleeve pipe formula grain structure

Info

Publication number: CN112922745B
Application number: CN202110365011.XA
Authority: CN
Inventors: 张群; 王紫欣; 王晓燕; 高耀红; 马晓曦
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2021-03-31
Filing date: 2021-03-31
Publication date: 2023-05-09
Anticipated expiration: 2041-03-31
Also published as: CN112922745A

Abstract

The invention provides a reverse rotation sleeve type grain structure, wherein a spiral groove structure is arranged on the inner surface of a sleeve type outer grain and the outer surface of a central grain, and the rotation direction of the outer grain spiral groove and the rotation direction of the central grain spiral groove are reverse. The gas also can the back removal of burning surface when the inside flow of grain, when the gas flows through this structure, spiral structure can make the gas produce the whirl, make the turbulent viscosity and the temperature gradient on grain surface bigger, and then improved grain surface heat flux density, strengthened grain surface heat convection, the propellant burning rate has been showing to improve, groove structure then makes the inside vortex that produces of gas, simultaneously because outside grain spiral groove's the spiral direction is opposite with the spiral direction of central grain spiral groove, two gas can form the impact, the inside disturbance increase of gas, the corresponding increase of turbulent flow, this structure makes fuel burning more abundant. The invention greatly increases the burning speed and is beneficial to more fully burning fuel.

Description

Contrary rotation type sleeve pipe formula grain structure

Technical Field

The invention relates to the field of solid rocket engines, in particular to a counter-rotating sleeve type grain structure.

Background

Modern war is largely a relatively high amount of space strength, and air-to-air missiles are the primary weapons of capturing the winnings of air combat. The solid rocket engine is characterized in that all solid propellants are filled in a combustion chamber, a supply system is not provided, and a propulsion system is a missile subsystem for providing power for missile flight and obtaining required flight speed and range of a missile. Along with the increasing energy of solid propellant, the increasing range of combustion speed, the increasing advanced of charging process and the application of thrust vector device, solid rocket engine as the propulsion system of air-to-air missile, compared with liquid rocket engine, the solid rocket engine has more and more superiority.

The solid propellant is placed in one or more of the combustion chambers in a manner known as a cartridge. The operating time of the engine, the combustion chamber pressure and the thrust are all related to the geometry and dimensions of the grain, which also affect the structural integrity of the grain and the mass ratio of the engine and the ratio of the mass of the propellant to the total mass of the engine. The rate of combustion of the fuel in the combustion chamber is the most important propellant characteristic in determining the internal ballistic process. At rated pressure it should be sufficient to achieve the performance required of the engine unit. In this case, the strength requirement does not allow the adoption of a plurality of grains with enlarged combustion surface, and a possible solution is to use an adherent charging mode, but in the condition that the combustion surface is limited, the required gas generation amount must be ensured at a high combustion speed, so that the only reliable method for improving the combustion speed is to improve the structure of the grains, and simultaneously, the fuel is combusted more fully to obtain larger energy and thrust.

Disclosure of Invention

Compared with the prior art, the technical problem to be solved by the invention is to provide a reverse rotation sleeve type grain structure, the reverse rotation sleeve type grain structure has the advantages that on the basis of the geometric shape of the traditional sleeve type grain, the spiral groove structure is arranged on the inner surface of the outer side grain, the spiral groove structure is also arranged on the outer surface of the central grain, the grooves are round, the resistance of high-temperature gas in the flowing process can be reduced to a certain extent, the loss of energy is reduced, the rotation direction of the spiral groove of the outer side grain and the rotation direction of the spiral groove of the central grain are reverse, the grain structure ensures that when the high-temperature gas flows, a part of the gas generates rotational flow and vortex due to the spiral structure on the inner surface of the outer side grain, so that the high-temperature gas burns more fully, and the other part of the high-temperature gas continues to flow forwards along the spiral groove on the outer surface of the central grain, the combustion speed is increased to a certain extent, and the flame turbulence is formed on the outer surface of the inner side grain due to the fact that the rotation direction of the spiral groove of the outer side grain and the spiral groove of the central grain are reverse, and the flame turbulence is formed on the outer surface of the inner side grain is increased, so that the flame turbulence is formed.

Technical proposal

The invention aims to provide a counter-rotating sleeve type grain structure.

The technical scheme of the invention is as follows:

a reverse rotation sleeve type grain structure, comprising: spiral groove structures are arranged on the inner surface of the outer circular ring grain and the outer surface of the central cylinder of the sleeve type grain, and spiral grooves are arranged on the inner surface of the outer circular ring grain and the outer surface of the central cylinder in a spiral direction. The anti-rotation sleeve type grain structure is characterized in that: the spiral groove is circular, the radius is 50-100 mm, and the pitch of the spiral groove is 40-100 mm.

The anti-rotation sleeve type grain structure is characterized in that: the spiral groove structures arranged on the inner surface of the outer circular ring grain and the outer surface of the central cylinder of the sleeve type grain are opposite in rotation direction.

The invention has the following beneficial effects:

compared with the existing ordinary sleeve type grain of the solid rocket engine, the invention has the advantages that the invention is remarkable and mainly represented by: spiral groove structures are arranged on the inner surface of the outer circular grain and the outer surface of the central grain, high-temperature fuel gas can form vortex inside the groove when flowing through the spiral groove structures, and a backflow area can be formed to enable the propellant to be fully combusted, so that larger energy and thrust are obtained. The spiral structure makes the fuel gas generate rotational flow when the fuel gas flows along the axial direction, so that the forward resistance of the fuel gas is weakened, the turbulent viscosity and the temperature gradient on the surface of the explosive column are larger, the heat flux density on the surface of the explosive column is further improved, the convective heat exchange on the surface of the explosive column is enhanced, the burning speed of the propellant is obviously improved, and the grooves are circular, so that the resistance of the high-temperature fuel gas in the flowing process can be reduced to a certain extent, and the energy loss is further reduced. Meanwhile, the spiral groove structures arranged on the inner surface of the outer circular grain and the outer surface of the central grain are opposite in rotation direction, two fuel gases can form impact and are mutually restricted, the internal disturbance of the fuel gases is increased, the turbulence level is correspondingly increased, the residence time of flame is increased to a certain extent, and the fuel combustion is more sufficient. The invention greatly increases the burning speed, is favorable for more complete combustion of fuel, so as to obtain larger energy and thrust and obtain more excellent inner ballistic performance.

Drawings

Fig. 1: integral structure schematic diagram of counter-rotating sleeve type grain structure

Fig. 2: counter-rotating sleeve type grain structure is along grain axial top view

Fig. 3: a section view of a counter-rotating sleeve type grain structure along the direction of A-A of top view

Fig. 4: schematic diagram of spiral groove rotation direction inside anti-rotation sleeve type grain structure

In the figure: 1-outer annular grain, 2-spiral groove structure on inner surface of outer annular grain, 3-spiral groove structure on outer surface of center annular grain, 4-center grain

Detailed Description

The invention will now be further described with reference to the accompanying drawings:

fig. 1 is a schematic view of the overall structure of a reverse rotation type sleeve type grain structure, fig. 2 is a plan view along the axial direction of the grain, so that the layout mode of the grain structure can be seen, and fig. 3 and fig. 4 are a cross-sectional view of the reverse rotation type sleeve type grain structure along the direction of A-A of the plan view and a schematic view of the rotation direction of an internal spiral groove respectively, so as to determine the distribution mode of the spiral groove and the relative position thereof.

The high-temperature fuel gas in the combustion chamber flows along the axial direction after ignition, when flowing through the

spiral groove structures

2 and 3 arranged on the inner surface and the outer surface of the annular explosive column 1, the high-temperature fuel gas can form vortex inside the groove to form a backflow area so that the propellant is fully combusted, and the groove is circular, so that the resistance of the high-temperature fuel gas in the flowing process can be reduced, and larger energy and thrust can be obtained. Meanwhile, high-temperature fuel gas can generate rotational flow when flowing through the spiral structure, the spiral groove structures arranged on the inner surface of the outer circular grain and the outer surface of the central grain are opposite in rotational direction, so that two fuel gases can generate impact, the two fuel gases are mutually restricted, the internal disturbance of the fuel gases is increased, and the turbulence level is correspondingly increased. The invention greatly increases the burning speed, is favorable for more complete combustion of fuel, so as to obtain larger energy and thrust and obtain more excellent inner ballistic performance.

Claims

1. A reverse rotation sleeve type grain structure, comprising: the inner surface of the outer circular ring grain and the outer surface of the central cylinder of the sleeve grain are provided with spiral groove structures with the same structure, the spiral groove structures are circular, the radius size range is 50-100 mm, the pitch of the spiral groove structures is 40-100 mm, and the spiral groove structures arranged on the inner surface of the outer circular ring grain and the outer surface of the central cylinder of the sleeve grain are opposite in rotation direction.