RU2671449C2 - Ampoule with starting fuel for ignition of fuel components of liquid fuel rocket engine - Google Patents

Abstract

FIELD: rocket equipment.SUBSTANCE: invention relates to the field of rocket technology, in particular, to devices for chemical ignition of fuel components for liquid-propellant rocket engines. Ampoule with starting fuel for ignition of fuel components of liquid fuel rocket engine, containing a power cylinder filled with starting fuel, two membrane assemblies with an inlet and an outlet channel, their membranes are made with an annular thinned bridge and they are fixedly sealed on the side of the entrance and exit of the power cylinder, in addition, the ampoule has means for rupturing the membranes, for fueling the power cylinder with starting fuel, and means for fixing the movable elements of the membranes after they have ruptured, each of the membrane assemblies includes a housing on one side of which a membrane is fixed, and on the other side a plug is mounted, a pyro drive consisting of a cylindrical guide and a piston with a rod, and a cylindrical shank is attached to the rear side of the membrane, which is connected to the rod, in addition, the supernumerary cavity through the opening in the body is connected to the cavity of the union in which the pyrotechnic charge is installed, wherein the diameter of the piston is greater than the diameter of the part of the membrane to be cut, and the connection between the cavity of the power cylinder and the inlet and outlet channels is carried out through the annular gap formed by rupturing the membrane and then moving it. In addition, the means for refueling the cylinder with the starting fuel consists of the filling and discharge nozzles, inside which the sealing plugs are installed; device for fixing the piston includes a split spring ring inserted into the annular groove formed on the piston of the pyro drive, and a groove made in a cylindrical guide for a pyro drive, the diameter of which is greater than the diameter of the piston; In the design of the ampoule an additional piston retainer is inserted, which includes a cone on the back of the piston and a tapered hole formed in the plug of the membrane assembly; perforated grilles are installed inside the power cylinder from the entrance and exit side.EFFECT: invention provides a simplification of the engine start system and increase of its reliability.5 cl, 1 dwg

Description

The invention relates to the field of rocket technology and, in particular, to devices for chemical ignition of fuel components of rocket engines.

To date, many different ignition schemes for non-combustible components have been developed and are in operation. For example, chemical, pyrotechnic, and electric spark ignition are widely used. In addition, work is underway to use laser ignition of components.

Known ampoule with starting fuel for ignition of the fuel components of the liquid propellant rocket engine, comprising a housing with an inlet and an outlet, two membrane assemblies, the membranes of which are hermetically fixed around the periphery in the housing from the inlet and outlet sides, (book. "Design and Design of the LRE" edited by G . G. Gakhuna. M: Engineering, 1989, p. 75, Fig. 4.5). In the known construction of the ampoule, membrane nodes with free-break membranes are used.

In this technical solution, the membrane breaks under the influence of the pressure of the medium, and the bending of the membrane (opening of the bore) is carried out by the pressure drop on it, which is determined, in particular, by the flow rate of the liquid. If the liquid flow rate and, consequently, the pressure drop across the membrane are small, then the membrane, firstly, can only break through partially, and, secondly, can bend by an arbitrary amount.

The disadvantage of this device is that it contains a starter tank, gas pressure accumulator, automation units, which complicates the engine starting system and the engine circuit as a whole.

Known chemical ignition unit (the book. "Design and Design of LRE" edited by GG Gakhun. M .: Mashinostroenie, 1989, p. 89), which contains a pre-chamber filled with gaseous oxygen, a launch tank with standard fuel, a sleeve with free-break membranes and automation units.

When the engine starts, the liner membranes break and the starting fuel is supplied to the pre-chamber. As a result of this, self-ignition of gaseous oxygen with starting fuel takes place in the pre-chamber and the formation of a combustion center. The resulting high-temperature combustion products enter the nozzle mounted on the mixing head and ignite the fuel and oxidizer that entered there earlier.

Such an ignition system works quite reliably. According to this scheme, the F-1 engine of the Saturn-5 launch vehicle (USA) was launched.

However, to start such a system, high fuel pressure is required to rupture the ampoule membranes.

From the source (patent RU No. 2159353, IPC F02K 9/95, 2000), an ampoule with starting fuel for igniting non-combustible fuel components is known, comprising a housing with input and output channels. Inside the housing are membrane units with free-break membranes. Moreover, the membrane is hermetically connected to the housing with the possibility of rupture. The ampoule design includes means for refueling the housing with starting fuel, a piston that is part of the membrane and means for refueling and fixing the movable part of the membranes after they rupture. The prototype of the invention.

To rupture the membranes, a high pressure of standard fuel of the order of 30–40 MPa is required, supplied from the launch tank, designed for this pressure.

A launch system with such an ampoule, possessing all the positive characteristics, can nevertheless be improved by eliminating the starting tank, gas pressure accumulator, and a complex control system that includes a large number of automation units from the circuit.

Disclosure invention

The objective of the invention is to create a new design of the ampoule, in which the membranes are ruptured using a pyrotechnic actuator triggered by a pyrotechnic charge, and the starting fuel is extruded from the ampoule using standard fuel with a pressure equal to the pressure of the gyrostatic column in the tank and the gas boost pressure.

This problem is solved due to the fact that the ampoule with starting fuel for igniting the fuel components of the liquid propellant rocket engine contains a power cylinder filled with starting fuel, two membrane assemblies with input and output channels, the membranes of which are made with a thinned ring jumper, and which are sealed tightly from the input side and the output of the power cylinder, in addition, the ampoule has means for rupturing the membranes, for refueling the power cylinder with starting fuel and means for fixing the movable elements of the membranes after they rupture, each of the membranes of these nodes includes a housing, on one side of which a membrane is fixed, and on the other hand, a plug is installed, a pyrodrive is installed inside the housing, consisting of a cylindrical guide and a piston with a rod, and a cylindrical shank is attached to the back of the membrane, which is connected to the rod, in addition, the supra-piston cavity is connected through a hole in the housing to the nozzle cavity in which the pyrotechnic charge is installed, the piston diameter being larger than the diameter of the membrane being cut off, and the cavity connection The first cylinder with inlet and outlet channels is carried out through an annular gap formed when the membrane ruptures and its subsequent movement.

Other differences are:

- means for filling the cylinder with starting fuel consists of filling and drain fittings, inside of which sealing plugs are installed;

- means for fixing the piston includes a split spring ring inserted into the annular groove made on the pyrodrive piston and a groove made in the cylindrical pyrodrive guide, the diameter of which is larger than the diameter of the piston;

- an additional piston retainer is introduced into the ampoule design, which includes a cone on the rear side of the piston and a conical hole made in the plug of the membrane unit;

- inside the power cylinder, perforated grids are installed on the input and output side.

The technical result consists in simplifying the engine starting system by eliminating from it a gas accumulator of the pressure of the launch tank with high pressure and reducing the number of automation units.

List of drawings

In FIG. a scheme of the longitudinal section of the ampoule is proposed.

An example embodiment of the invention

The ampoule (Fig. 1) contains a power cylinder 1 filled with starting fuel 2, two membrane units 3 and 4 with inlet and outlet channels 5 and 6, while the membrane unit 3 is connected to the main fuel supply line, and the membrane unit 4 is connected to the pipeline introducing starting fuel into the mixing head of the gas generator or into the volume of the combustion chamber (not shown). Since the membrane nodes have the same design, the membrane node 4 will be partially digitized in the description. Each of them includes a housing 7, on one side of which a membrane 8 is fixed with an annular thinned jumper 9, and on the other hand, a plug 10 is installed. Inside of the housing 7, a pyrodrive is installed, consisting of a cylindrical guide 11, a piston 12 with a rod 13. A cylindrical shank 14 is attached to the back of the membrane, which is connected to the rod 13. The diameter of the piston is larger than the diameter of the rod. The supra-piston cavity 15 is connected through a hole 16 in the housing to the cavity 17 of the nozzle 18. The cavity 17 is designed to accommodate a pyrotechnic charge (not shown) in it. Two annular grooves are made on the outer surface of the stem, into which the sealing rings 19 are inserted. These rings prevent the ingress of solid particles from the pyrotechnic charge from the over-piston cavity 15 into the output channel 6 of the membrane assembly 4. The connection of the cavity of the power cylinder 1 with the input and output channels 5 and 6 is carried out through an annular gap 20, which is formed upon rupture of the membranes 8 and their subsequent movement. Inside the power cylinder 1, on the input and output sides, perforated gratings 21 and 22 are installed, which provide an equal starting fuel flow over the entire cross section of the power shell.

For filling the ampoule with starting fuel, two fittings are installed on the outer surface of the power cylinder 1 - filling 23 and drain 24, inside of which sealing caps 25 and 26 are installed.

The ampoule design also includes two piston retainers — a spring retainer 27 and a cone-to-cone retainer 28. The spring retainer 27 includes a split spring ring 29 inserted in an annular groove made on the pyrodrive piston 12 and a groove 30 made in a cylindrical guide 11 pyrodrive, the diameter of which is larger than the diameter of the piston. As a result, when moving the piston 12, the ring 29, unclenching, enters the groove 30, and the piston 12 is locked.

An additional piston retainer 12 is introduced into the ampoule design, which includes a cone 31 located on the rear side of the piston 12 and a cone hole 32 made in the plug 10. When the piston is moved, the cone 31 enters the cone hole 32 and stops due to friction forces.

The use of two clamps makes it possible to reliably fix the piston after rupture of the membranes and prevent its reverse movement.

The device operates as follows

Before starting the engine in the input membrane unit, the pyrotechnic charge located in the cavity 17 of the nozzle 18 is undermined, and due to the action of the compressed gas from the combustion products on the unloaded piston area, a force is created, which leads to the movement of the piston 12 and the breakthrough of the membrane 8 in the membrane unit 3. B As a result, the standard fuel from the tank under a pressure equal to the pressure of the hydrostatic column and the boost pressure in the tank enters the channel 5 of the membrane unit 3, then enters the annular gap 20 and then into the power cylinder 1 through the per orirovannuyu grating 21 to contact with the starting fuel.

When the engine starts, a command is issued to undermine the pyrotechnic charge located in the cavity 17 of the nozzle 18, the output membrane unit 4. Under the action of the powder gases, the piston 12 moves and the membrane 8 breaks, and the standard fuel is under pressure equal to the pressure at the inlet to the power cylinder 1, squeezes the starting fuel from the ampoule into the pipeline, and from it into the mixing head of the gas generator or the firing volume of the engine chamber. After moving the piston 12 to the extreme position, it is fixed using a spring retainer 27 and a cone-by-cone type 28 retainer.

The use of a pyrotechnic drive for rupture of membranes can significantly simplify the engine starting system and reduce its cost.

Industrial application

The most successfully declared ampoule can be used in the line of one of the fuel components at the entrance to the mixing head of the combustion chamber or gas generator for chemical ignition of the fuel components.

Claims (5)

1. An ampoule with starting fuel for igniting the components of a liquid propellant rocket engine containing a power cylinder filled with starting fuel, two membrane assemblies with input and output channels, the membranes of which are made with a thinned ring jumper and which are sealed tightly from the input and output sides of the power cylinder, in addition , the ampoule has a means for rupture of the membranes, for refueling the power cylinder with starting fuel and means for fixing the movable elements of the membranes after rupture, characterized in that each of the membrane nodes including it includes a housing, on one side of which a membrane is fixed, and a plug is installed on the other side, a pyrodrive consisting of a cylindrical guide and a piston with a rod is installed inside the housing, and a cylindrical shank is attached to the back of the membrane, which is connected to the rod, in addition, the supra-piston cavity is connected through a hole in the housing to the nozzle cavity in which the pyrotechnic charge is installed, the piston diameter being larger than the diameter of the membrane being cut off, and the connection of the power cylinder cavity with the input the bottom and outlet channels are carried out through an annular gap formed during rupture of the membrane and its subsequent movement. 2. The ampoule according to claim 1, characterized in that the means for refueling the cylinder with starting fuel consists of filling and drain fittings, inside of which sealing plugs are installed. 3. The ampoule according to claim 1, characterized in that the means for fixing the piston includes a split spring ring inserted into an annular groove made on the pyrodrive piston and a groove made in a cylindrical pyrodrive guide, the diameter of which is larger than the diameter of the piston. 4. The ampoule according to claim 1, characterized in that an additional piston retainer is introduced into the ampoule design, which includes a cone on the back of the piston and a conical hole made in the plug of the membrane assembly. 5. The ampoule according to claim 1, characterized in that perforated grids are installed inside the power cylinder from the input and output sides.

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