| 摘要 |
FIELD: motors and pumps. ^ SUBSTANCE: invention relates to rocket-ramjet engine designs of long-run operation and used particularly for supersonic cruise missiles. Gas generator of rocket ramjet engine consists of a body with front and rear lids, nozzle, end-burning charge made of highly metallised fuel and gas conduit fixed on the front and rear lids of gas generator. Solid fuel charge is ensured with armored covering on all sides, except the end directed to the front lid. Solid fuel charge is strongly fastened to gas conduit crossing charge channel with protective and fixing layer. Gas conduit orifice area is from 5 to 20% from charge burning surface area. Perforation is made in the upper part of gas conduit, on the arc no more than 180° and at an angle no less than 30° to gas conduit axis and in the direction of gas generator nozzle. Perforations diameter is no more than 20% from gas conduit walls thickness. Total perforated area dimensions do not exceed 30% of the internal gas conduit surface. ^ EFFECT: improved power characteristics of engine due to metal particle of highly metallised fuel release from gas generator combustion chamber during the long period. ^ 4 dwg |
