FIELD: engines and pumps.
SUBSTANCE: gas turbine engine compressor comprises rotor with vanes and stator with outer and inner casings jointed together by taper flange. Compressor has also blow-down chamber and perforated deflector. Note also that radial but of taper flange with inner casing is arranged between the inlet and outlet edges, first from the circular groove arranged between air intake chamber and compressor flow section. Flanged nozzle made in deflector is directed towards said vane. Note here that the angle between compressor flow section outer wall generatrix and stator front flange outer surface, nearby circular groove, makes α=40°…80°.
EFFECT: higher efficiency of gas turbine engine compressor due to reduced radial gap between stator and rotor for vane, first behind of intake chamber, in all operating conditions.
2 dwg
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