RU2326340C2 - Method for disposal propellant charges of solid-fuel rocket engines - Google Patents

Abstract

FIELD: methods of ammunition disposal.

SUBSTANCE: the method consists in extracting charges from an engine , their mechanical longitudinal cutting into uniform sticks with a maximum cross-section size not exceeding 100 m, placing said charge sticks vertically one over another into oil producing and injection wells filled with fluid and their burning in the near-wellbore zone. Charge sticks are delivered to the burning zone by means of a wire-line in a cylindrical container perforated with holes for products effluence in the central portion of the side face at a distance of 1/4 of the length from the both end faces, and then the sticks are burnt over their outer surfaces inflaming them by sending electric pulses simultaneously to the both igniters disposed on the bottom end face of the bottom stick and on the top end face of the top stick. According to the second variant, the container is perforated over its entire side face. The charge sticks are burnt over their end faces from top downward, by inflaming the top end face of the top stick.

EFFECT: ensuring reduction of disposal costs, enhancing technological effectiveness and environmental safety of the process.

2 cl, 3 dwg

Description

The invention relates to methods for utilizing the solid charges of solid propellant rocket engines (solid propellant rocket engines).

The following methods are best known for the disposal of solid propellant solid propellant charges:

- equipment for training ammunition, equipment for test devices with a short service life, equipment for special explosive devices for civilian purposes;

- processing charges from ballistic fuels into civilian products (industrial explosives, paints and varnishes, anticorrosion coatings, lubricants, etc.) / A.V. Kostochko “Special polymers and compositions”, Kazan, “Matbugat Yorty” publishing house, 1999 , p. 153-156, p. 182-196; “Armament. Policy. Conversion ”Information and analytical journal RARAN, 2002, No. 5, pp. 40-42;

RF patents No. 2176230, С06В 21/00, F42В 33/06, F42D 5/04;

No. 2215720, С06 В 21/00, С05F 11/00, F42В 33/06;

No. 2232739, C06B 21/00, F42B 33/06, F42D 5/04;

RF application No. 2002118664/02, F42В 33/06, 1/02 /.

All of the above methods for utilization of solid propellant solid propellant charges have significant drawbacks that limit their widespread use: environmental pollution, large investments in the creation and maintenance of recycling facilities, a low degree of processing of materials received from recycling, and low cost of their sale at a high cost of transportation.

There is a method of disposing of solid charges of solid propellant rocket engines according to the application RU 97118483/02, F42В 33/06, which consists in the fact that the charges are removed from the engines and cut longitudinally into the same type of pieces using special equipment. Checkers are booked on the lateral surface and installed alternately in a container with support on each other along the end surfaces. The container together with the tubing string is lowered into a fluid-filled oil producing or injection well and installed in the bottomhole zone of the reservoir in the perforation interval of the casing string. The annulus of the well is sealed with a packer mounted above the container. The checkers are burned alternately on the end surface from top to bottom, igniting the upper checker by applying an electrical impulse to the electric igniter via a geophysical cable connected to the console. In this way, the solid propellant charges are utilized, using them simultaneously for thermobarochemical treatment of the bottom-hole zone of the oil producing well in order to intensify oil production. This method of utilizing solid propellant charges is the closest to the claimed one and can be used as a prototype.

The main disadvantages of the prototype:

- the delivery of the container with solid fuel drafts to the well treatment zone is carried out on the tubing string, i.e. Before disposal, installation of the tubing is necessary, and after - the dismantling of the tubing string. Given the very high complexity of the work associated with the installation and dismantling of the tubing string, this method of disposal is not always economically feasible;

- the use of a tubing string to deliver a container with solid fuel checkers makes it impossible to use a geophysical cable and cable head to supply an electrical pulse to an electric igniter, therefore a single-wire electrical circuit with a movable contact is used, which significantly reduces the reliability of ignition;

- the use of armored end-combustion charges significantly reduces the range of charges to be disposed of, and makes it necessary to use a packer to seal both tubing and annular space, as It is almost impossible to provide the necessary pressure impulse in the processing zone with the help of end-combustion charges without a packer. Using a packer complicates the recycling process.

The technical task of the present invention is the development of an environmentally friendly, safe method of disposal of solid rocket solid propellant charges, allowing with great economic effect to use solid propellant solid propellant charges after mechanical cutting or without cutting for thermobarochemical treatments of low production wells in order to intensify oil production.

The proposed method involves the utilization of solid charges of solid propellant rocket motors, in which the charges are removed from the engines, cut longitudinally into several pieces, depending on the initial diameter of the charge so that the maximum size in the cross section of the checker is not more than 100 mm. The pieces obtained after cutting are mounted vertically on top of each other in a cylindrical container supported by end surfaces. The container is connected using a cable head with a cable and lowered into a fluid-filled well in the perforation interval of the casing. Solid fuel checkers are burned, igniting simultaneously the upper and lower of them by applying an electric pulse to an electric igniter. It is possible to ignite by applying an electric pulse only to the top block.

This technical result is ensured due to the fact that the used operations of extracting plug-in charges from the engines, cutting them, installing them in containers, delivering them to the bottom-hole zone of the well and burning are based on well-known proven technologies that are widely used at present. The environmental safety of the method is ensured by the combustion of solid fuel blocks in sealed wells at great depths in the environment of water, oil, solutions of salts, acids. High temperature and high pressure contribute to the occurrence of chemical reactions of the interaction of combustion products with the environment. Thus, the authors propose a method for the controlled burning of solid propellant charges in underground closed-type volumes with the complete neutralization of combustion products. This method of disposal is carried out with minimal economic costs, because engine demineralization and longitudinal cutting of charges are not laborious, do not require the creation of special production facilities and can be carried out at equipment factories, and their subsequent burning in wells, as a rule, is combined with repair and maintenance work during well operation. A significant economic effect of this method of disposal is obtained by thermobarochemical treatment of the productive formation of the well, which occurs during the combustion of solid fuel elements, and expressed in the form of an increase in oil recovery.

Figure 1 presents a diagram of the implementation of the proposed method for the disposal of external charges of solid propellant rocket engines.

Charges are removed from the engines and cut longitudinally on special equipment into the same type of checkers (Figs. 2, 3) depending on the initial diameter of the charge so that the maximum size in the cross section of the checker is not more than 100 mm. Checkers 6 are mounted vertically on top of each other with support on end surfaces in a cylindrical refillable container 5 perforated along the side surface with openings for the expiration of combustion products. At the lower end of the lower checker and the upper end of the upper one, electric igniters 3 are installed. The electric wires from the electric igniters 3 are connected to the cable cable 1 through the cable head 2. The container 5 on the cable cable 1 is lowered into the well filled with liquid and installed in the perforation interval of the casing string 7. From the wellhead through the cable-cable 1, an electrical impulse is supplied to the electric igniters 3. When the electric igniters 3 are activated for a limited time (0.1-0.3 s), all solid-fuel elements ki 6. The combustion of the checkers 6 lasts from 0.5-5 s depending on the burning rate of the fuel, the size of the cross section of the checkers 6, the pressure in the combustion zone. Combustion is accompanied by a large heat release (850-900 kcal / kg), gaseous products (1000 l / kg at P = 0.1 MPa), therefore, along with utilization of solid propellant charges in low-rate oil producing wells, thermobarochemical treatment of bottom-hole is carried out zones of the productive formation 4. The technologies of low-oil production and injection wells using solid fuel charges have been widely used over the past 30 years. These technologies are based on the use of high pressure, high temperature, and chemical reactions of combustion products with the rock of formation 4 to increase the permeability of the productive formation 4. In this case, the permeability of the formation 4 increases due to its rupture with the formation of artificial fracturing with a pressure exceeding the rock pressure, or due to heating the formation 4 to the melting temperature of the asphaltene-resinous and paraffin deposits in the pores of the formation 4, followed by their removal by the flow of oil into the well. High pressure exceeding the mountain pressure is achieved by selecting the surface and burning speed of the checkers 6 installed in the container 5. During short-term charge combustion (0.5-1 s), the column of well fluid located above the container 5, due to inertia and friction against the wall of the well, immobile during the entire time the charge is burning and acts as a packer, due to which pressure exceeds the mountain pressure in the combustion area, which leads to fracture of formation 4. An indispensable condition for solving the problem of fracturing of formation 4 is The realization of charge energy in the shortest possible time, i.e. obtaining the necessary pressure pulse, which is possible only with the simultaneous ignition of the surface of all the pieces 6. To ensure reliability and quality of ignition, the lower and upper parts of the container 5 to 1/4 of its length are not perforated with holes. The absence of holes on the side surface of the container 5 in the area of electric igniters 3 forces the combustion products having a temperature T = 2500 ° C to move between the container body 5 and the solid fuel blocks 6, displacing the wellbore fluid, warming and igniting the blocks 6. This solution allows for reliable simultaneous ignition of the entire surface of the solid fuel drafts 6 in difficult conditions of finding a charge in the well fluid. In those cases when, due to the design features of the well, it is impossible to expose it to high dynamic loads, the selection of the burning rate and dimensions of the checkers 6 is carried out in order to ensure a low gradient of pressure rise and an increased burning time of the checkers 6, i.e. the thermal energy of the fuel is used to a greater extent for heating the productive formation 4 and cleaning it by melting substances that plug the pores of the formation 4. In this case, the charge burning time is increased by selecting checkers 6 with a lower burning rate, and the charge is burned from top to bottom, igniting the upper end face of the upper pieces. To prevent ignition of the side surface of the drafts 6, the entire lateral surface of the container 5 is perforated. In this case, displacement of the well fluid by combustion products from the cavity between the container 5 and the drafts 6 along the entire charge length becomes impossible, therefore, combustion occurs along the end surface, moving from top to bottom along the length of the charge, and the borehole fluid wetting the side surface prevents its ignition, acting as an armor coating. This type of combustion provides a small gas intake and creates excess pressure insufficient to fracture the formation 4, on the other hand, increasing the burning time of the charge contributes to a deeper heating of the formation 4 and can be used to clean the bottom-hole zone of the productive formation 4.

The novelty of the proposed method of utilization of solid propellant solid propellant charges lies in the fact that their delivery and destruction by burning are carried out in reusable containers autonomously lowered into the combustion zone. The combustion of charges is combined with the treatment of the bottom-hole zone of the productive formation of oil producing and injection wells in order to increase oil recovery. The design of the container is selected depending on the nature of the processing of the well.

Claims (2)

1. A method for utilizing the solid charges of solid-propellant rocket engines, including removing the charges from the engine, mechanically cutting them into pieces of the same type with a maximum cross-sectional dimension of not more than 100 mm, laying the blocks vertically on top of each other in oil producing and injection wells filled with liquid and burning them in the bottomhole zone of the wells, characterized in that the pieces are delivered to the combustion zone on a cable cable in a cylindrical container, perforated holes for the expiration of products the central portion of the side surface, spaced apart by 1/4 of the length from the both ends, and is burned on the outer surfaces of checkers, igniting them simultaneously supply both electric pulse igniter disposed at the lower end and the lower checkers on the upper end of the top checkers. 2. A method for utilizing the solid charges of solid-propellant rocket engines, including removing the charges from the engine, mechanically cutting them into pieces of the same type with a maximum cross-sectional dimension of not more than 100 mm, laying the blocks vertically on top of each other in oil producing and injection wells filled with liquid and burning them in the bottomhole zone of the wells, characterized in that the pieces are delivered to the combustion zone on a cable cable in a cylindrical container, perforated holes for the expiration of products Goran across the side surface and burn them on the end faces downward, igniting the upper end surface of the top checkers.

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