HYBRID PROPULSION ENGINE CAPABLE OF EXPANDING THE MINIMUM OPERATIONAL MACH NUMBER OF A DUAL RAMJET TO 2.0

摘要

PURPOSE: A hybrid propulsion engine is provided to supersonically discharge a subsonically combusted fuel-air using a tandem nozzle in order to lower the minimum operational Mach number of an engine to 2.0, thereby expanding the operational range of an entire dual ramjet.;CONSTITUTION: A hybrid propulsion engine includes a main body(110), a complex combustor(130), a gas generator(140), and a variable flow path valve(142). The complex combustor continuously operates in a ramjet mode and in a scramjet mode. In the ramjet mode, a tandem nozzle chokes a subsonically combusted gas in the complex combustor in order to supersonically discharge the gas. In the scramjet mode, air flows in the gas generator so that the gas generator can pre-combust fuel and air which are to be combusted in the complex combustor. The variable flow path valve shuts off the gas generator in the ramjet mode. The variable flow path valve is open in the scramjet mode, and transfers the flow path of the air in order to make part of the air flowing into a hollow portion(111) flow into the gas generator.;COPYRIGHT KIPO 2013;[Reference numerals] (150) Propeller control unit; (AA) Variable flow path valve opening signal; (BB) Tandem nozzle stop signal; (CC) Mach; (DD) Altitude