Patent ID: 6551056
Filing Date: 2003-04-22
Classification: F01D,F02C

Abstract:
A cooling air ducting system of a high-pressure turbine section of a gas turbine engine in which a portion of an air flow which exits from a compressor section of the engine bypasses a combustion chamber of the gas turbine, comprising:a pre-swirl chamber positioned upstream of a first stage turbine rotor disk; a diaphragm separating the pre-swirl chamber from an interior of the engine; a first pre-swirl system provided in the diaphragm for ducting a portion of the bypass air flow into the pre-swirl chamber to air-cooled blades carried by the first stage turbine rotor disk to cool the blades; and a second pre-swirl system positioned in the diaphragm radially inwardly from the first pre-swirl system for ducting a further portion of the bypass air flow into the pre-swirl chamber to a radially inwardly portion of a face of the first stage turbine rotor disk.