FIELD: engines and pumps.
SUBSTANCE: combustion chamber of the liquid rocket engine consuming the fuel components - liquid oxygen and liquid hydrogen, or liquid oxygen and the liquefied natural gas, containing the ignition device, the chamber housing with fuel supply main lines for cooling, the mixing head with the fuel supply main lines, the gas passage with the main line of supply of oxidizing generating gas connected to the ignition device by means of the flange located on the external surface with the cooling path channels implemented in it which is fixed by one end with the flange, and is installed by another one in the central bushing of the mixing head housing. The flange for installation of the ignition device is located on a side surface of the gas passage of the mixing head and has a manifold ring, cooling path channels of which are connected to the curved bushing cooling channels by means of the ring faceplate, and the ignition device cooling path channels are connected to the flange manifold by means of the tube.
EFFECT: decrease of weight, simplification of fastener design and improvement of reliability of engine swinging.
2 dwg
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