HEAT TRANSFER IN HIGH-PRESSURE COMPRESSOR GAS TURBINE INTERNAL AIR SYSTEMS: A ROTATING DISC-CONE CAVITY WITH AXIAL THROUGHFLOW

摘要

This article reports on heat transfer measurements made on a rotating test rig representing the internal disc-cone cavity of a gas turbine high-pressure (H. P.) COMPRESSOR STACK. Tests Were carried out for a rang of flow rates and rotational speeds at engine representative Nondimensional conditions. The rig also had a central drive shaft, which could rotate in The same direction as the discs, contrarotate relative to the discs. Or remain static.