Cooling air ducting system in the high pressure turbine section of a gas turbine engine

Abstract

This invention relates to a cooling air ducting system in the high-pressure turbine section of a gas turbine engine, in which a portion of the air flow which exits from the compressor section of the engine and bypasses the combustion chamber of the gas turbine is ducted via a first pre-swirl system provided in a diaphragm into a pre-swirl chamber arranged upstream of the first stage turbine rotor disk and is fed from this pre-swirl chamber, in particular, to the air-cooled blades of this rotor disk for cooling purposes, and in which another portion of this air flow is applied to the face of the first stage turbine rotor disk via a second air transfer system which, when viewed in the radial direction, is arranged further inward than the first pre-swirl system. According to this invention, the second air transfer system is again provided as a pre-swirl system connecting to the pre-swirl chamber. Preferably, a sealing system is provided between a section of the diaphragm which confines the pre-swirl chamber and the turbine shaft section adjacent to this diaphragm section, this sealing system being less permissive of leak air than the labyrinth-type seals commonly used in this application.

Dependencies are inferred from the claim text.