GAS TURBINE ENGINE COOLING SYSTEM AND METHOD

摘要

Fuel (12) supplied to a rotary fluid trap (42) is centrifugally accelerated within a first cavity (46) adjacent a first side (48) of a rotor (24), and i s then directed though a plurality of first passages (66) extending through th e rotor (24) between and proximate to the blades (26), and shaped so as to at least partially conform to the shape of the blades (26). Second passages (10 0) extend within the blades (26) from the first passages (66) and terminate within associated cavities (110) proximate to the tips (112) of the blades (26). Relatively cooler fuel (12.2) in the first passages (66) is thermosiph on exchanged for relatively hotter fuel (12.3) in the second passages (100) so as to cool the blades (26). The heated fuel (12.3) flows into a second cavity (74) adjacent to a second side (72) of the rotor (24) and is discharged from the rotating frame of reference directly into the combustion chamber (16) through a second rotary fluid trap (96). A separate fuel distribution circui t (130) is used for starting and warm-up.