RU2164617C1 - Gas generator - Google Patents

Abstract

FIELD: jet engines. SUBSTANCE: gas generator of solid-propellant jet engine has housing with bottoms and side service holes accommodating solid propellant charge limited by end faces of grids. Each mushroom-shaped grid is connected with housing bottom by its base. Grid is provided with one or several central slots from side of charge to housing bottom. Service holes are located opposite to grid bases. Diameter of grid base is 0.6-0.8 of end face diameter. EFFECT: improved efficiency of jet engine and gas generator. 2 dwg

Description

 The invention relates to a device for jet engines of solid fuel (RDTT) and gas generators (GG) and can be used in objects with multi-plate charges placed in a housing with an off-center (side) arrangement of nozzles (flow openings), used, for example, to create a lateral control jet forces in systems of correction and control of the trajectory of ammunition.

 Lattices are used as a support charge element in solid-state solid-propellant rocket engines and multi-plate charges.

 The grill is a cylindrical washer installed in front of the nozzle or consumable hole (s). The lattice perceives flight and gas-dynamic loads and, at the same time, prevents charge residues from escaping into the nozzle when it is destroyed at the end of combustion.

 For this purpose, a lot of holes (axial grooves) are made on the grate or, at the end facing the charge, parallel slots are milled to a certain depth according to the type of grate.

 At the same time, the cross-section of the channels of the lattice that is free for gas passage is 3-5 times larger than the critical section of the nozzle or the supply opening (M.E.Serebryakov. Internal ballistics of barrel systems and powder rockets. Moscow. Oborongiz, 1962, 242, 270) .

 In small-sized solid propellant solid-propellant rocket engines and gas condensates, in particular with charges with a short burning time, the latter condition is difficult to fulfill because of the relatively large critical cross section of the nozzle (feed hole) and the lattice channels being inevitably blocked by the support surface of the charge.

 The desire to increase these channels by increasing the diameter of the holes or the width of the slots (of course, with a reduction in their number) makes the grating ineffective for retaining charge residues in the chamber at the end of combustion, as a result of which the thrust (reactive) impulse of the solid-propellant rocket engine and gyrometer is reduced and the required ballistic characteristics are not fulfilled , for example, operating time due to a decrease in the level of working pressure when ejecting fuel residues.

 When installed behind a nozzle or flow hole, made sideways in the chamber wall, which is often caused by the layout of the solid propellant rocket and gas turbine on the object (for example, to orient the control force vector perpendicular to the axis), such gratings become generally ineffective.

 The present invention aims at increasing the efficiency and improving the design of small-sized solid propellant rocket motors and gas turbines with lateral flow openings in the direction of increasing the implementation of the total thrust impulse (pressure) by eliminating the discharge of charge residues.

 In our opinion, this is achieved by making the gratings mushroom-shaped, connected by a base to the bottom of the casing, as well as by making central slots from the charge side to the bottom of the casing and placing nozzles (consumable openings) opposite the bases of the gratings.

 The essence of the proposed technical solution is illustrated by the drawing.

 Here is a typical design of a small-sized gas generator with a solid fuel charge 1 in the form of a tube package placed in a housing 2 with lateral flow openings 3 perpendicular to the axis of the gas generator.

 On the one or the other side, the bottom 4 is screwed into the housing 2, turning into lattices 5, between which a charge 1 is placed.

 From the side of the charge at the ends of the gratings there are grate ledges 6, on which the charge rests.

 Lattices 5 are given a mushroom shape. The diameter of the base of the grating d relative to the diameter of the end face D is 0.6 ... 0.8.

Higher d / D ratios, as can be seen from the table of experimental data, lead to a sharp decrease in the efficiency of the gratings from the point of view of realizing the total thrust impulse J _R due to the discharge of charge residues, and lower ones to an unaccounted pressure increase.

 To increase the total area of the channels free for gas passage, from the charge side in the gratings 5, one or more central slots 7 are made to the bottom of the body. Achieved at the same time, an increase in the area of bore cross sections (by 4 ... 10 times) ensures gas-dynamic stability of the engine working process.

 The proposed technical solution is experimentally justified by testing a small-sized gas generator of a warhead missile dilution system, including flight design, factory and state tests.

Claims (2)

 1. A gas generator comprising a housing with bottoms and side flow openings, a solid fuel charge placed therein, limited by the ends of the grids, characterized in that each grill is made mushroom-shaped and connected to the bottom of the housing by a base, and one or more central slots are made in it from the charge side to the bottom of the housing, while the consumable holes are located opposite the bases of the gratings.  2. The gas generator according to claim 1, characterized in that the diameter of the base of the lattice is 0.6 ... 0.8 of the diameter of its end.

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