GAS-TURBINE ENGINE INTAKE SYSTEM BLADE Russian patent published in 1999 - IPC

FIELD: mechanical engineering. SUBSTANCE: intake system blade of gas-turbine engine is provided with upper and lower fastening members. Longitudinal channel is made in inlet edge of blade feather. This channel communicates with air feed channel in upper part of blade and with blading of gas-turbine engine through holes in blade wall on upper and lower end faces of longitudinal channel. Swirling device, for instance, in form of cross, is made at outlet of air feed channel. Hole made in end face of longitudinal channel adjoining swirling device has diameter equal to 0.6-0.9 of channel diameter and is located in center. Longitudinal channel has round section. EFFECT: increased temperature of inlet edge of blade feather. 4 cl, 3 dwg