HIGH PRESSURE COMPRESSOR ROTOR THERMAL CONDITIONING USING OUTER DIAMETER GAS EXTRACTION

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 hi...

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Bibliographische Detailangaben
Hauptverfasser:	FORCIER, Matthew P, HIESTER, Paul J, ACKERMANN, William K
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	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.