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 is then directed though a plurality of first passages ( 66 ) extending through the 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 ( 100 ) 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 thermosiphon 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 circuit (130) is used for starting and warm-up.