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CONDITIONNEMENT THERMIQUE DE ROTOR DE COMPRESSEUR À HAUTE PRESSION AU MOYEN D'EXTRACTION DE GAZ DE DIAMÈTRE EXTERNE
CONDITIONNEMENT THERMIQUE DE ROTOR DE COMPRESSEUR À HAUTE PRESSION AU MOYEN D'EXTRACTION DE GAZ DE DIAMÈTRE EXTERNE
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摘要
A compressor (100) for use in a gas turbine engine comprises a compressor rotor including blades (104) and a disc (102), with a bore (102A) defined radially inwardly of the disc (102). A radially outer housing (107) surrounds an outer diameter of the blades (104). A lower pressure tap (108) and a higher pressure tap (110) tap air from two distinct locations within the compressor (100) and radially outwardly through the outer housing (107). A valve (112) selectively delivers at least one of the lower pressure tap (108) and the higher pressure tap (110) to the bore (102A) of the disc (102). A control (113) for the valve (112) is programmed to move the valve (112) to a position delivering the higher pressure tap (110) at a point prior to take-off when the compressor (100) is mounted in a gas turbine engine on an aircraft.
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