Gas turbine engine having a cooled turbine
AssigneeROLLS-ROYCE plc
InventorHenry Tubbs
Life of this patent
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Abstract
A gas turbine engine is disclosed in which a particularly efficient use of cooling air is made. In this engine, at least part of the cooling of the turbine blades is effected by a bleed of air from one of the compressors. This bleed air is ducted to flow between the shanks of adjacent rotor blades to cool them, and the used bleed air then rejoins the main gas flow of the engine upstream of the turbine rotor.
Claims14
A gas turbine engine having a cooled turbine, a compressor wall having apertures therein for the flow of compressor bleed air from the main engine airflow, first duct means for directing the bleed air to flow to said turbine, the turbine comprising a rotor disc carrying a row of rotor blades each having a root portion, a shank portion and an aerofoil portion, said first duct means directing said bleed air between the shanks of adjacent blades to cool them, and second duct means for conveying the bleed air from the tubine rotor into the main gas flow of the engine upstream of the turbine rotor.
Dependencies are inferred from the claim text.