RU2347180C2 - Method of cooling solid-propellant rocket engine channel and charge combustion products during liquidation of rocket engine and device to this effect (versions) - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to liquidation of the solid-propellant rocket engine charge at the test bench equipped with the chamber of localisation and to cooling the combustion products. The proposed method comprises the system designed to feed coolant into the charge channel. On the front cover of the rocket engine to be liquidated, a two-chamber tapered spraying module with slot-like and cylindrical holes is mounted and connected with the water line of coolant module water feed and accumulation via a multi-purpose valve. First 10 to 20% of water-salt solution of potassium chloride is fed via independent line to the spraying module, then, when the charge is completely burnt out, water from a common water supply manifold is fed. Two versions of the device are presented for embodiment of the aforesaid method. Safe and optimum liquidation conditions are ensured by cooling the channel and combustion products via spraying with coarse-dispersed coolant through the spraying module.

EFFECT: safe conditions of liquidation.

3 cl, 8 dwg

Description

The invention relates to rocket technology, namely, to the elimination of the charge of a solid propellant rocket engine at a stand equipped with a chamber for localization and cooling of combustion products.

The main objective of the proposed method and devices is to provide optimal (adjustable), safe conditions for the expiration of the combustion products into the chamber of localization and cooling of the combustion products during the elimination of the charge of a rocket engine using solid fuel.

The cooling of the charge channel and the generated combustion products of a solid propellant rocket engine during its elimination leads to a decrease in the initial energy parameters of the expiration of the combustion products (pressure in the channel, the rate of expiration of the combustion products, temperature, traction) by affecting the rate of formation and development of the initial combustion surface.

Upon completion of the charge elimination process, the remaining fuel is quenched and the internal surface of the burning building is cooled, which is important for maintaining the integrity of the building and reducing the release of toxic components into the atmosphere (environmental safety).

The well-known "Method of eliminating the charge of solid rocket fuel", in which the channel of the liquidated charge is cooled, which is in the vertical position with a refrigerant - water, alkaline or soda solution, Patent RU 2021560 C1, op.15.10.94, IPC F23G 7/00.

As a prototype of the method, the authors adopted patent RU 2021560 C1.

The disadvantages of this prototype include the following:

1. The absence of spray modules for the formation of a coarse atomized stream of refrigerant for cooling the charge channel and the resulting combustion products in order to control the process and the rate of formation of the initial combustion surface of the liquidated charge of a solid propellant rocket engine;

2. In Patent RU 2021560 C1, the channel of the charge being eliminated is cooled by filling the entire charge channel with water, an alkaline or soda solution through the front cover of the rocket engine in its vertical arrangement.

The main disadvantages of this method of cooling the channel of a liquidated missile charge are:

- the vertical location of the rocket engine on solid fuel and further structural (geometric) characteristics of the stand for localization and cooling of the resulting combustion products. This method is almost impossible to apply to large-sized, multi-tonnage solid propellant rocket engines with a length of 5 ... 7 m and a mass of 30 ... 50 t, since their vertical position requires the development of complex fasteners, stands, which can lead to an emergency;

- the pressure of the refrigerant on the surface of the charge channel and on its combustion products is very negligible and is determined by its mass located at the given moment in the charge channel. As practice shows, under such conditions, the refrigerant is “squeezed” by the combustion products from the channel, since the combustion products have the greatest dynamic and speed characteristics (pressure, flow rate) in comparison with the refrigerant.

Known atomization devices, combined nozzles and other mechanical devices for atomizing the refrigerant used in high-speed automatic fire-fighting systems (BAPS) for extinguishing fires, where various atomization devices are used to provide atomized and compact jets when refrigerant, in particular water, flows through them. "Guidelines for the design and operation of automatic fire protection systems for the production of plastics and polymers." RUE-APZT-T, Central Research Institute of NTI, 1977.

Channel NK-ZRS nozzles specified in RUE-APZT-T, page 34, were adopted as a prototype for the device.

The disadvantages of the prototype on the device include the following:

- the design does not provide slot holes for the formation of beam jets, irrigation and cooling of combustion products in the rays and branches of the channel of the liquidated charge;

- it was established experimentally that the NCC type nozzles used in various mechanical and combined spray structures form a finely dispersed stream of refrigerant that is unable to penetrate deeply into the gas stream of the combustion products of the liquid being eliminated and reach the combustion surface.

The technical task of the claimed inventions is to increase technological safety during the elimination of the bulky charge of a solid propellant rocket engine, including defective products, with their horizontal arrangement. This problem is solved by creating optimal conditions for the combustion of a charge on a stand equipped with a containment chamber and cooling the combustion products, as well as protecting and preserving the rocket engine casing from burning and its further destruction in the process of burning the charge.

Regulation by the process of the outflow of combustion products into the containment and cooling chamber by cooling the channel and the resulting combustion products of the liquid being eliminated reduces the temperature and pressure of the combustion products, which accordingly reduces the level of impact of the high-speed, high-temperature gas flow on the structure as a whole and leads to an increase in the service life of the containment chamber and cooling, excluding the occurrence of emergency situations in the form of burning through the walls of the chamber or its destruction when exceeding the inside back pressure.

The technical result of the method is that:

1. A two-chamber conical spray module with slotted and cylindrical holes is installed on the front cover of the liquidated rocket engine and connected to the water supply line of the storage and water supply module with the refrigerant through the shut-off and start-up device of the system with a speed of not more than 5 s, and served as a refrigerant to the spray module initially 10-20% aqueous-salt solution of calcium chloride through an independent water supply line, consisting of a storage tank with a volume of 300 ... 600 m ³ , a receiver with a working pressure of 0.8 ... 1.6 MPa and a compressor to fill the receiver with compressed air, and upon completion of the charge burning process, water is supplied from a common water supply collector, while the flow rate, depending on the design of the spray module and pressure within 0.2 ... 1.6 MPa, is 0.02 ... 0.1 m ³ / s.

The technical result on the device is presented in two versions:

Option 1:

1. A two-chamber beam conical spray module with slit and cylindrical holes for cooling the channel and the products of the charge of a rocket engine with a complex channel configuration, consists of the first conical chamber with equally spaced openings with a diameter of 4 ÷ 6 mm in the amount of 30 ... 40 pieces and a refrigerant distributor in the first a spray module chamber with 5 ... 7 slots 0.5 × 10 mm wide, and a second conical chamber with slotted slots 40 ... 60 mm long, 10 ... 20 mm wide with an opening angle of 40 ° in the amount of 3 ... 6 pieces and scattering castors with a diameter of 40 mm with holes with a diameter of 30 mm and 3 ... 6 holes with a diameter of 30 mm, for supplying refrigerant to the second chamber of the spray module.

Option 2:

2. The two-chamber end spray module with slotted and cylindrical openings for cooling the channel and combustion products of a rocket engine with a smooth-bore channel configuration consists of a first conical chamber with equally spaced openings with a diameter of 4–6 mm in an amount of 30 ... 40 pieces and a refrigerant distributor in the first chamber with 5 ... 7 slots with a width of 0.5 × 10 mm and a second chamber with 4 circular slots 40 ... 60 mm long with an opening angle of 40 ° and a cylindrical divider with a diameter of 40 mm with 6 holes with a diameter of 30 mm and a 6th slot with a width of 10 × 15 mm, for supplying refrigerant to the second chamber of the spray module.

3. For both the first option and the second one, a central conical nozzle is installed in the center of the spray module of the second chamber to form a compact jet with a refrigerant spray diameter of 20–30 mm at the base.

The proposed invention allows to carry out:

- control (regulation) of the combustion process of the charge of the rocket engine by cooling the channel and the resulting products of combustion of the liquidated charge by the refrigerant through the spray module with the specified hydraulic parameters (pressure, flow), using an independent system for accumulating and supplying the spray module with refrigerant;

- providing conditions for the penetration of the refrigerant due to the formation of a coarse atomized stream of refrigerant in the formed products of combustion of the liquidated charge;

- localization and cooling of combustion products in a charge channel having a complex geometric profile (rays, branches, etc.);

- determination and fulfillment of optimal safe conditions for the expiration of combustion products, liquidated solid-propellant rocket engine into the chamber for localization and cooling of the test bench by reducing the rate of formation of the initial combustion surface and, accordingly, the speed and flow parameters of the expiration of combustion products;

- reducing the risk of unstable combustion of defective engines after a long shelf life by reducing the pressure of the combustion products in the charge channel, their flow rate and temperature of the combustion products;

- providing conditions for increased cross-flow of the refrigerant through the flame during the joint use of a high-flow atomization module and the use of 10-20% aqueous-salt solution of calcium chloride CaCl ₂ ;

- additionally, the freezing temperature of 10-20% water-salt solution of calcium chloride CaCl ₂ is minus 10 ... 15 ° C, which allows its use in the winter season on open areas of the stand.

The pressure of the spray module when supplying refrigerant, depending on the liquidated charge of the rocket engine (mass, composition, burning rate, etc.) is determined by calculation, but not less than 0.2 MPa, since at low pressures (experimentally established) a stable atomized flow of refrigerant is formed, and the condition for its penetration into the depths of the combustion products is not fulfilled.

The locking and starting equipment of the system is launched remotely via the control panel or in automatic mode using a time timer within 1 ... 5 s from the start of the initiation of fuel charge.

The invention is illustrated by schemes in two versions:

Figure 1 shows a schematic diagram of the main elements of the entire system cooling the channel and the generated combustion products during the elimination of the charge of a solid propellant rocket engine, where:

1 - receiver (gas holder) for creating pressure in the system - 1.6 MPa, 2 - storage tank for refrigerant with a capacity of 300 ... 600 m ³ , 3 - common collector of water supply, 4 - liquidation charge of a rocket engine using solid fuel, 5 - sections of the containment chamber and cooling the combustion products of a rocket engine, 6 - a water supply line for the spray module with a refrigerant, 7 - a line for supplying a spray device with a refrigerant, 8 - a front cover of a rocket engine, 9 - an atomized stream of refrigerant, 10 - a flame torch.

Figure 2 schematically shows the strait of the channel and the housing of the liquidated rocket engine on solid fuel, where:

11 - a lodgement for installation and fastening of a liquidated rocket engine, 12 - a two-chamber beam conical spray module and the principle of formation of a sprayed refrigerant stream.

The device according to option 1:

Figure 3 shows the installation diagram of the beam two-chamber conical spray module on the front cover of the liquidated solid propellant rocket engine.

Figure 4 shows a disassembled beam two-chamber conical spray module with slotted and cylindrical holes for localization and cooling of the channel of the liquidated rocket engine using solid fuel, where:

13 - conical distributor with 3 ... 6 slotted openings for creating atomized radiation flow of refrigerant, for localization and cooling of combustion products in the rays of the charge channel of the rocket engine and the output of the central compact stream for cooling the flame in the central part of the channel, 14 - divider for the formation of beam spray jets, 15 - truncated conical distributor for the formation of compact jets with equally spaced holes with a diameter of 4 ÷ 6 mm in the amount of 30 ... 40 pieces, 16 - refrigerant distributor in the first the spray unit with the second chamber 5 ... 7 0,5 × slit width of 10 mm, 17 - the back of the spray module cover.

Figure 5 shows the second chamber of the spray module for forming atomized beam jets and a central compact jet, as well as water conduits and dividers for supplying a second chamber with refrigerant and forming beam atomized jets, where:

18 - dividers for creating a 6-beam refrigerant flow (if necessary, the number of radiation openings can be reduced to 3 ^x ), at the bottom of each divider there is an opening for refrigerant to enter the second chamber, the upper part of the divider is muffled;

19 is a central conical nozzle for creating a central compact jet.

The device according to option 2:

Figure 6 shows the installation diagram of the end two-chamber spray module with slotted and cylindrical holes for localization and cooling of the smooth-bore channel of the liquidated charge of the rocket engine, where:

20 - end two-chamber spray module with slotted and cylindrical holes.

In Fig.7 shows an exploded view of the end dual-chamber spray module with slotted and cylindrical openings for the exit of the refrigerant, where:

21 - a second chamber for creating a sprayed radiation stream of refrigerant around the circumference of the channel of the liquidated charge of the rocket engine; 22 - conduit and divider for feeding and forming a beam coarse atomized stream.

On Fig is a diagram of the water conduit and divider to create a radiation stream of refrigerant in the second chamber of the end atomization module and the central compact stream, where:

24 - holes for the entrance of the refrigerant into the divider, 25 - holes for the exit of the refrigerant from the divider.

Both versions of the device have the same purpose and are aimed at obtaining the same technical solution: cooling the channel and the resulting combustion products of the liquidated charge of the rocket engine on solid fuel, but having a different channel configuration.

The technical solution in the proposed method and device is implemented as follows:

1. Fill the receiver (1) with air to the required pressures, and the storage tank (2) with refrigerant - 10-20% aqueous-salt solution of calcium chloride CaCl ₂ .

2. On the front cover of the solid fuel rocket engine (8), depending on the configuration of the charge channel (the presence of rays, branches, etc.), a two-chamber conical spray module with slot and cylindrical holes (12) or an end two-chamber spray module with slot holes (20) for supplying refrigerant to the charge channel, which is connected by an accumulation and water supply system (Figs. 1, 3, 5).

3. The front cover (8) with the spray module is mounted on the rocket engine and connected to the water supply line through the locking and starting equipment (6, 7).

4. After initiating the charge of the rocket engine (4), the coolant in the form of an atomized coarse stream providing cooling of the channel and the formed products of combustion of the liquidated charge is supplied to the channel of the liquidated charge under pressure through the spray module (12 or 20) (Fig. 2).

5. The refrigerant through the water supply line (6, 7), respectively, after the locking and starting equipment is opened, enters through the distributor (16) into the first chamber of the spray module (12 or 20) and exits in the form of compact jets through conical openings, after filling the first chamber, the refrigerant enters through the inlet openings (18 or 24) into the internal cavity of the dividers (14 or 22), then the refrigerant leaves the holes of the divider (18 or 25) and fills the internal cavity of the second chamber of the spray module (12 or 20), then goes around the dividers (14 or 22) exits through the slots of the spray module to the outside, forming a coarse atomized radiation beam stream of refrigerant.

The refrigerant also enters the central conical nozzle (19) of the second chamber of the spray module (12 or 20) and comes out in the form of a compact jet.

6. After the cessation of the formation of the active torch and the completion of the elimination of the charge, water is supplied to the rocket engine housing from the common water supply manifold (3), opening the shut-off and starting equipment of the water supply line (6) to extinguish the remaining fuel and cool the internal surface of the housing.

7. The type of two-chamber spray module, pressure, time and hydraulic parameters of the flow of refrigerant are determined for each solid fuel rocket engine separately taking into account the characteristics (burning time, mass) and the configuration of the charge channel.

8. As a result of supplying a highly dispersed, coarse stream of refrigerant through a two-chamber spray module, the following conditions are fulfilled:

- cooling the surface of the channel of the liquidated charge and a decrease in the velocity of propagation of the combustion front over the surface of the liquidated charge;

- penetration of the refrigerant into the depths of the flame, cooling of the combustion products and, as a result, - reduction of the temperature of the combustion products;

- as a result of a decrease in the speed of propagation of the flame on the inner surface of the channel and the temperature in the channel of the liquid being eliminated, the pressure of the expiring combustion products into the containment and cooling chamber decreases;

- decreases the rate of formation of the initial combustion surface in the channel of the liquidated charge.

Experimental studies conducted by FSUE “NIIPM” in studying the conditions for extinguishing combustion sites at the ends of various solid rocket fuel compositions and for localizing the flame produced by the developed high-dispersion atomization modules forming a coarse atomized refrigerant stream, as well as when using 10-20% as a joint refrigerant water-salt solution of calcium chloride CaCl ₂ - showed the possibility of regulating the combustion processes of the charge of a rocket engine with their fuel-free burning anany.

Claims (3)

1. A method of cooling a solid fuel charge channel of a rocket engine and solid fuel combustion products during charge elimination, comprising supplying refrigerant to the charge channel, characterized in that a two-chamber conical spray module with slot and cylindrical openings is installed on the front cover of the rocket engine and connected to a water conduit the accumulation and water supply lines of the module with the refrigerant through the locking and starting device of the system with a speed of not more than 5 s, as a coolant in the spray mode s serves initially 10 ... 20% aqueous solution of calcium chloride salt of an independent water supply line consisting of a storage container of 300 ... 600 m ^3, the receiver with a working pressure of 0.8 ... 1.6 MPa and the compressor to fill compressed air receiver and upon completion of the charge burnout process, water is supplied from a common water supply collector, while the flow rate, depending on the design of the spray module and pressure within 0.2 ... 1.6 MPa, is 0.02 ... 0.1 m ³ / s. 2. A beam two-chamber conical spray module for cooling the channel and the products of the charge of the rocket engine during its elimination, containing a refrigerant mixing chamber, a central conical nozzle, characterized in that it consists of a first conical chamber with equally spaced openings with a diameter of 4 ... 6 mm in an amount of 30 -40 units and a refrigerant distributor in the first chamber of the spray module with 5-7 slots 0.5 × 10 mm wide and the second conical chamber with slotted slots in the length of 40 ... 60 mm, in the width of 10 ... 20 mm with an angle of hiding 40 ° in the amount of 3-6 pieces and dividers with a diameter of 40 mm with holes with a diameter of 30 mm and 3-6 holes with a diameter of 30 mm for supplying refrigerant to the second chamber of the spray module. 3. End two-chamber conical spray module with slotted and cylindrical holes for cooling the channel and combustion products of a rocket engine during its elimination, containing a refrigerant mixing chamber, a central conical nozzle, characterized in that it consists of a first conical chamber with equally spaced openings with a diameter of 4 ... 6 mm in the amount of 30-40 pieces and a refrigerant distributor in the first chamber with 5-7 slots 0.5 × 10 mm wide and the second chamber with 4 circular slots 40 ... 60 mm long with an opening angle of 40 ° and 40 mm diameter cylindrical divider with 6 holes with a diameter of 30 mm and 6 slots with a width of 10 × 15 mm for supplying refrigerant to the second chamber of the spray module.

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