AXIAL-FLOW NULTISTAGE COMPRESSOR OF GAS-TURBINE ENGINE Russian patent published in 2003 - IPC

FIELD: mechanical engineering; gas turbine engines. SUBSTANCE: invention relates to gas turbine engines used to drive supercharger in gas transfer sets. Proposed axial-flow multistage compressor of gas turbine engine has turnable vanes of guide-vane assembly of one or several inlet stages. Said vanes are multiposition and turning at constant degree of pressure rise in group of last 3- 4 stages of compressor. For this purpose compressor is additionally furnished with air pressure transmitters at inlet and outlet of group of last stages and with automatic control device containing pressure rise degree calculator in group of last stages and vane turning control unit of guide-vane assemblies. Input of calculator is connected with pressure transmitters and, outlet is connected with inlet of vane turning control unit, which, in its turn, is connected by outlet with vane turning mechanism. Invention enlarges working power range by changing capacity of compressor at preservation of reserve of gas dynamic stability and economy of engine. EFFECT: enlarged operating capabilities. 2 dwg