ROTOR RIM OF AXIAL-FLOW COMPRESSOR (FAN) OF TURBOJET ENGINE

摘要

FIELD: mechanical engineering: turbojet engines. SUBSTANCE: proposed rim of rotor of axial-flow compressor (fan) of turbojet engine contains profile blades with linear section directed in parallel to blade incoming flow. Rim consists of blades of two types installed in two rows shifted forward and backward in front relative to each other. Blades with linear section are located on forward shifted row, and blades with arbitrary profile are located in backward shifted row. Moreover, blades of different types can have different length of chord profile. Such design makes it possible to eliminate noise arising when supersonic flow passes over peripheral part of rim and preserve tolerable characteristics (π_c and efficiency). EFFECT: reduced noise. 2 cl, 2 dwg