FIELD: turbines or turbomachines.
SUBSTANCE: compressor (10') of gas turbine engine comprising at least one annular row of stator blades (12) with variable installation angle, wherein these blades are substantially radial and contain trunnions (22, 24) on their radial ends, wherein radially external blades pins are installed in first holes of stator housing (20) and radially internal trunnions are installed in second holes of floating ring (60), which surrounds rotor (18) of compressor, characterized by that between floating ring and compressor rotor there is annular part (62) of stator, and the fact that between the stator part and the compressor rotor the first sealing means are installed and between the floating ring and the stator part the second sealing devices are installed.
EFFECT: decreased internal diameter of the compressor flow path.
7 cl, 3 dwg
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