RU2397352C1 - Water supply device in section of combustion products containment and cooling chamber for solid propellant rocket engine charge liquidation - Google Patents

Abstract

FIELD: power industry.

SUBSTANCE: water supply device in section of combustion products containment and cooling chamber for solid propellant rocket engine charge liquidation comprises water distributing pipeline and spray nozzles. Arch-shaped spray nozzles are designed to generate pulverised water flux in the form of dispersed conical screen. Arch screen-generating spray nozzles are installed on water distributing pipeline inside of combustion products containment and cooling chamber section in amounts of 4 to 16 pieces per combustion products containment and cooling chamber section. Each arch screen-generating spray nozzle comprises 3 to 6 inlet fittings with diametre 20 to 40 mm, arch deflector with diametre 40 to 70 mm, which has 5 to 20 mm wide slotted opening with 45° expansion angle, and internal distributing cylinder with diametre 20 to 40 mm and openings for water outlet into mixing and reflecting chamber in amounts of 8 to 20 pieces.

EFFECT: effectivisation of combustion products cooling by pulverised large particle water flux.

5 dwg

Description

The invention relates to rocket technology, and in particular to a device for eliminating the charge of a solid propellant rocket engine by burning on a stand equipped with a chamber for localization and cooling of combustion products.

A modern bench complex for testing and eliminating solid-fuel rocket engines is a complex engineering facility with unique, expensive equipment, support, control systems, as well as a set of systems for localizing, cooling and neutralizing combustion products.

The bench complex is used for work with various solid propellant rocket engines, differing in size, weight (from 4 ... 50 t), solid fuel and burning time. Accordingly, the elimination of such solid propellant rocket engines requires conditions that exclude the walls of the containment and cooling chamber sections from being burnt by the high-speed, high-temperature gas flow of the combustion products when it expires.

In this case, it is necessary to ensure optimal conditions for the expiration of the combustion products in the semi-enclosed space of the sections of the chamber for localization and cooling of the combustion products, excluding the creation of pressures exceeding the strength characteristics of the structures as a whole.

The well-known "Method of monitoring and control of the thermal regimes of the expiration of the combustion products in the chamber for localization and cooling of the combustion products during the liquidation of a solid propellant rocket engine and a device for its implementation": RF Patent No. 2309280, op. 10.27.07, IPC F02K 9/24.

The well-known "Method of eliminating the charge of a large solid propellant rocket engine without a nozzle block by the combustion method": RF Patent No. 2301959, op. 06/27/07.

As a prototype, the authors adopted RF patent No. 2309280, op. 10.27.07, IPC F02K 9/24, declared 09/05/2005.

The general disadvantages of these devices and methods include the following.

1. In all sections of the chamber for localization and cooling of combustion products, cylindrical nozzles forming a compact stream are used as atomizing devices, and adjustment of such nozzles is impossible due to the fact that they are firmly fixed to the distribution water supply pipe to the sections.

2. The small contact area of the coolant (compact jet) with the combustion products does not allow to achieve lower temperatures inside the sections of the chamber for localization and cooling of the combustion products during the entire combustion process of a solid propellant rocket engine.

3. The possibility of eliminating the charge of a solid propellant rocket engine with a low gas intake due to braking and locking of the combustion products inside the sections of the chamber for localization and cooling of the combustion products is difficult.

The technical task of the invention is to increase technological and environmental safety when eliminating the charge of a solid propellant rocket engine at a stand equipped with a chamber for localization and cooling of combustion products by increasing the efficiency of cooling combustion products by a sprayed coarse stream of water.

The tasks in the invention are solved by:

- replacement of cylindrical nozzles (in the prototype) with arc screening spray nozzles (DERN) along the entire circumference and length of the section of the chamber for localization and cooling of combustion products;

- creation of coarse, cone-shaped, water screens inside the section, providing cooling efficiency by increasing the contact area and the breakdown ability of the combustion products of a liquidated solid fuel rocket engine;

- improving the cooling efficiency of the combustion products by changing the angle of the sprayed water flow through the DERN relative to the movement of the combustion products inside the sections and their quantity;

The technical result of the device containing the distribution conduit and spray nozzles is achieved due to the fact that the spray nozzles are made of arc with the possibility of forming a sprayed stream of water in the form of a coarse, conical screen, and the arc screening spray nozzles are installed on the distribution conduit inside the sections of the containment and cooling chamber combustion in an amount of 4 to 16 pieces for one section of the chamber for localization and cooling of combustion products, and each The arc screening spray nozzle contains inlet nozzles with a diameter of 20 to 40 mm in an amount of 3 to 6 pieces, an arc-shaped reflector with a diameter of 40 to 70 mm, including a slit-shaped hole with a width of 5 to 20 mm with an opening angle of 45 °, and an internal distribution cylinder with a diameter of 20 to 40 mm with holes for water to enter the mixing and reflection chamber in an amount of 8 to 20 pieces.

The proposed dimensions of the DERN are obtained as a result of experimental studies on the development of a spray nozzle.

The invention is illustrated by diagrams.

Figure 1 shows a schematic diagram of an arc screening spraying nozzle (DERN), where:

1 - an arched reflector, 2 - nozzles, 3 - slotted hole.

Figure 2 shows the inner distribution cylinder DERN, where:

4 - distribution cylinder; 5 - water supply from the storage system; 6 - water outlet from the distribution cylinder; 7 - holes for the exit of water from the distribution cylinder.

Figure 3 shows the arcuate reflector DERN, where:

8 - a chamber for mixing and reflection of water from the inner wall of an arc-shaped reflector; 9 - the output of the water stream and the formation of a coarse, conical water screen.

Figure 4 shows the layout of the DERN on the distribution conduit section of the chamber for localization and cooling of combustion products, where:

10 - nozzles for the entrance of water into the distribution conduit; 11 - distribution conduit; 12 - DERN; 13 - section housing of the chamber for localization and cooling of combustion products; 14 - node docking and adjusting the angle of supply of the sprayed stream of water from the DERN relative to the movement of the flow of combustion products; 15 - water inlet from the storage system with preset pressure parameters.

Figure 5 shows the adjustment scheme of the DERN and the angle of the sprayed water flow relative to the movement of the combustion products inside the section of the chamber for localization and cooling of the combustion products, where:

16 - the direction of movement of the products of combustion; 17 is the angle of supply of the sprayed stream of water relative to the movement of products of combustion, with 0 ° being the starting point of reference for rotation of the DERN, and 110 ° is the final reference point of turning of the DERN.

The cooling of combustion products using DERN is as follows.

1. Conduct preparatory work on the accumulation and supply of water with the specified pressure parameters through the pipes (10) into the distribution conduits of the sections of the chamber for localization and cooling of the combustion products (11).

2. Next, water (5) under pressure enters the DERN (12) through the docking unit (14) and inlet pipes (2), then into the distribution cylinder (4) and then water (6) through the holes (7) enters the mixing chamber and reflections (8) where, being reflected from the arc-shaped reflector (1), it leaves through the slot hole (3), forming a coarse, conical water screen (9) at a given irrigation angle (17).

3. The angle of supply of the sprayed stream of water (17) is selected from the conditions for the expiration of the combustion products (16).

The use of coarse, cone-shaped water screens can improve the cooling efficiency of the combustion products of a rocket engine by increasing the breakdown ability and increasing the contact area of water and combustion products.

The cooling efficiency of the combustion products and the conditions for their expiration in the semi-enclosed space of the localization and cooling sections is carried out by changing the angle of supply of the atomized stream and the amount of DERN used. For example, at high velocities of the expiration of combustion products up to 300 m / s and a relatively low temperature - use the largest angle of the sprayed water flow (110 °) and the smallest amount of DERN to exclude the braking conditions of the flow of combustion products and create increased pressure inside the sections, and at low flow rates or high temperature of the combustion products inside the sections - use the smallest angle of supply of the atomized stream of water or a larger number of DERN.

The number of installed arcuate screen-forming, spray nozzles (from 4 to 16 pieces), as well as their structural and geometric dimensions (diameters of inlet pipes from 20 to 40 mm and their number from 3 to 6 pieces, diameter of the arc-shaped reflector from 40 to 70 mm, diameter internal distribution cylinder from 20 to 40 mm) is determined based on the following indicators:

- geometric dimensions: the length, inner diameter of the sections of the chamber for localization and cooling of the combustion products, for example, with a section diameter of 3 m and a length of 5 m - the number of water conduits (11) is from 1 to 4 pcs., the DERN installation in the sections is carried out with an interval of 1 up to 2 m between them, on each water conduit for 4 pcs. DERN (not less);

- the distance the section is located from the liquidating charge of the rocket engine on solid fuel, that is, the farther the section, the lower the temperature of the combustion products (in the initial sections, the temperature ranges from 2500 to 3000 ° C, and in the end sections the temperature drops to 100 ° C ), therefore, there is no need to set the maximum number of nozzles in the end sections of the chamber for localization and cooling of combustion products;

- characteristics of the liquidation charge of a solid propellant rocket engine (flow rate, fuel consumption and temperature of the combustion products).

The indicated geometrical dimensions of the arc screening spray nozzles have been developed for the charges of solid propellant rocket engines with a consumption when burning without a nozzle from 100 to 300 kg / s and a temperature from 100 to 3000 ° C, at which efficient cooling of the combustion products is achieved by increasing the breakdown ability of coarse particles sprayed water flow. For example, with an inlet pipe diameter of 40 mm and an arc-shaped reflector diameter of 70 mm, the water flow rate (depending on the initial pressure in the system) is: at an initial pressure of 0.2 MPa - a flow rate of 21 l / s, and at an initial pressure of 0.6 MPa - flow rate is 39 l / s from one DERN.

If the inlet nozzles have diameters less than 20 mm and the arc-shaped reflector has a diameter of 40 mm, the cooling conditions of the combustion products are ineffective due to the fact that a coarse sprayed water stream is not formed, and with inlet diameters of more than 40 mm and an arc-shaped reflector 70 mm in diameter according to technical and economic indicators it is impractical, since high initial pressures in the system (more than 0.6 MPa) are necessary to form the required water flow.

Claims (1)

A device for supplying water to a section of a chamber for localization and cooling of combustion products during liquidation of a solid rocket engine charge, comprising a distribution conduit and spray nozzles, characterized in that the saw nozzles are arc-shaped with the possibility of forming a sprayed water stream in the form of a coarse cone-shaped screen, moreover arc-shaped spray nozzles mounted on a distribution conduit inside sections of the chamber for localization and cooling of combustion products in an amount of 4 to 16 pieces for one section of the chamber for localization and cooling of the combustion products, and each arc screening spray nozzle contains inlet pipes with a diameter of 20 to 40 mm in an amount of 3 to 6 pieces, an arched reflector with a diameter of 40 to 70 mm, including a slit-like hole with a width of 5 to 20 mm with an opening angle of 45 °, and an internal distribution cylinder with a diameter of 20 to 40 mm with holes for water to enter the mixing and reflection chamber in an amount of 8 to 20 pieces.

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