FIELD: engines and pumps.
SUBSTANCE: solid fuel flow control is arranged between a gas generator and an afterburner of a ducted rocket engine and includes a control device with a drive, an adjustable nozzle sleeve and a nozzle sleeve of constant flow cross-section, which connects the gas generator to the afterburner. The adjustable nozzle sleeve is installed in the gas generator wall and can supply gas generation products to the afterburner and is equipped with a control assembly of the flow cross section, which is connected to the drive of the control device. Inlet plane of the adjustable nozzle sleeve is offset inside the gas generator. The inlet plane of the nozzle sleeve of constant cross section coincides with the plane of the gas generator wall. The control assembly of the flow cross section is made in the form of a turning shaped damper of variable cross section. A thickened part of the shaped damper has the possibility of adjusting the flow cross section, and a thinner part has the possibility of protecting the adjustable flow cross section from straight inleakage of gas generation products.
EFFECT: invention allows improving reliability of a solid fuel control.
4 cl, 4 dwg
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