Foreign particle separator
AssigneeGeneral Electric Company
InventorsWalter E. Koster, William E. Ludke, Frank A. Lastrina
Life of this patent
Estimating the term…
Abstract
A particle separator for the air cooling system of a gas turbine engine is provided in the form of a rotating chamber having an inlet disposed radially outward of the engine centerline at a distance greater than the distance of the chamber outlet from the engine centerline. The rotation of the chamber centrifuges foreign particles away from the chamber outlet to provide for separation of the particles from the air exiting the chamber.
Claims4
In a system for cooling a blade associated with a gas turbine engine wherein said blade is adapted to rotate about an engine centerline, the invention comprising:
- a flow path receiving pressurized air and delivering said air to said blade;
- a rotating chamber, disposed in said flow path and adapted to rotate about said centerline;
- an inlet for introducing said air into said chamber, said inlet disposed at first radial distance from said centerline;
- an outlet means providing for the discharge of said air from said chamber, said outlet means having an entrance disposed at a second radial distance from said centerline, said second radial distance being less than said first radial distance thereby utilizing centrifugal force to generally prevent foreign particles in said air from entering said outlet means;
- and
- a pair of turbine discs at least partially enclosing said chamber disposed therebetween, said chamber bounded by a radially outer most wall disposed radially outwardly of said inlet, said wall including an aperture, said outlet means comprising an elongated hollow tubular element mounted within said aperture, said element having an entrance disposed radially inward of said inlet and an exit disposed radially outward of said inlet.
In a system for cooling a blade associated with a gas turbine engine wherein said blade is adapted to rotate about an engine centerline, this invention comprising:
- a pair of spaced-apart turbine discs adapted for rotation about said engine centerline, each of said discs including a flange extending axially toward the other of said discs;
- a torque ring disposed between and engaging each of said flanges, said ring including a plurality of mounting apertures extending radially therethrough;
- means for securing said ring and said discs in a fixed relationship with respect to one another;
- a plurality of blades fixedly secured to one of said discs at the outer periphery thereof, each of said blades having a cooling circuit therein;
- a rotating chamber disposed radially inward of said flanges and ring and at least partially bounded by said flanges and said ring and said disc;
- a plurality of inlets extending axially through one of said discs for admitting pressurized cooling air into said chamber, said inlets disposed at a first radial distance from said centerline;
- a plurality of elongated hollow tubular elements mounted in said mounting apertures in said ring, each of said tubular elements having an entrance disposed at a second radial distance from said centerline, said second radial distance being less than said first radial distance thereby utilizing centrifugal force to generally prevent foreign particles in said cooling air from entering said tubular element entrances, each of said tubular elements further having an exit disposed radially outward of said first radial distance;
- and means for communicating pressurized air discharged from said tubular members to said cooling circuit in said blades.
Dependencies are inferred from the claim text.