GAS TURBINE ENGINE WITH AXIAL COMPRESSOR WITH INTERNAL COOLING PATHWAYS

摘要

A gas turbine engine (10) may include an axial high pressure compressor having an air flow pathway (120) positioned between the inner and outer rim (112,110) of a rotor section. The air flow pathway (120) includes an inlet port (122), a transition segment (124), an axial segment (126), and an outlet port (128). The pathway (120) may be a tube having an ovoid cross sectional shape and is substantially co-planar to an outer surface (140) of the outer rim (110). The pathway (120) may traverse the rotor section from a first rotor segment (102) to a rear hub (130).