Gas turbine engine cooling system and method

Details Gas turbine engine cooling system and method Gas turbine engine cooling system and method

2005-04-25

2011-11-15

Wiehe, Nathaniel (Department: 3745)

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

C416S09600A

Reexamination Certificate

active

08057163

ABSTRACT:
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.

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