| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: proposed method comprises mixing air with fuel and feeding combustion mixture into resonator and detonation combustion of fuel in said resonator. Heat exchangers are arranged on resonator and thrust module outlet nozzles to be heated, prior to starting, to 200 to 800 C with the help of starting heaters. Liquid combustion fuel is compressed to 10 to 30 MPa and fed into heated heat exchangers to be evaporated and superheated. Vapor compressed to 10 to 30 MPa and superheated to 200 to 600 C is forced into ejector nozzles with its mixing chamber communicated with atmosphere. Aforesaid chamber mixes fuel vapors with air. Resulted combustible mix is forced into resonator, wherein it is detonation combusted. To force fuel into thrust modules, variable-capacity pump is driven by thermal engine triggered by electrical starter supplied from current source. Electric generator, driven from thermal engine, charges current source. Thrust modules are warmed up, prior to starting, by starting heaters supplied by current source. Supersonic jet from annular nozzle is broken into separate jets to form air passages there between. ^ EFFECT: higher thermal efficiency and specific thrust, simplified design, reduced cost and vibration. ^ 7 cl, 5 dwg |
