METHOD FOR PROTECTING TURBOEJECTOR ENGINE AGAINST STALL

摘要

FIELD: engines and pumps. ^ SUBSTANCE: bypass to low pressure channel of gas ejector at closed inlet of the channel is performed. At total degree of pressure increase in conditions of takeoff 3.54.0 of pressure increase degree in compressor before and after air takeoff are preferably equal. Bypass is preferably performed at flight speeds of less than two Mach numbers. Fuel can be supplied to low pressure channel of gas ejector. ^ EFFECT: possibility of excluding emission of hot gas to compressor inlet without deteriorating the engine characteristics. ^ 4 cl, 2 dwg