Fan blade assembly for a gas turbine engine
AssigneeFlorida Turbine Technologies, Inc.
InventorStephen E Murray
Life of this patent
Estimating the term…
Abstract
A small twin spool gas turbine engine with a forward end of the engine supported by bearings that are cooled by passing a cooling fluid such as cooling air bled off from the compressor with a liquid lubricant sprayed into the cooling air that is then passed through the bearing to prevent overheating. The cooling fluid is then discharged from the bearing cooling circuit out the front end of the engine through a number of discharge holes formed within the threaded nut that secures the fan blade assembly to the low speed rotor shaft. The threaded nut includes a plurality of slanted holes that slant outward from the rotational axis in the direction of fluid discharge.
Claims10
An axial compressor comprising:
- a compressor rotor disk with a plurality of blades extending out from the rotor disk;
- a compressor rotor shaft with one end of the compressor rotor shaft extending out from a central opening in the compressor rotor disk;
- a threaded nut securing the compressor rotor disk against axial displacement to the compressor rotor shaft;
- and,
- the threaded nut forms at least one cooling fluid passage connecting the forward side to the aft side of the threaded nut to allow for cooling fluid to be discharged from within the axial compressor.
Dependencies are inferred from the claim text.