Patent ID: 8092145
Filing Date: 2012-01-10
Classification: F02C,F04D,F05D,Y02T

Abstract:
1. A particle separator for a gas turbine engine having a central longitudinal axis, comprising a generally toroidal cavity defined within a casing surrounding a compressor impeller gas path and being in gas flow communication therewith through a plurality of circumferentially interspaced bleed apertures formed in said casing, the cavity being funnel-shaped such as to define a radially outer narrow tip circumferentially extending about the cavity, at least one clean air outlet being disposed in communication with the cavity and located radially inwardly from the radially outer narrow tip thereof, and a particle outlet radially located in a circumferential lower portion of the radially outer narrow tip of the cavity, the circumferential lower portion being disposed below the central longitudinal axis of the gas turbine engine in a normal flying attitude, the bleed apertures allowing bleed air from the compressor impeller gas path to flow into the cavity, during operation of the gas turbine engine, with a tangential velocity component sufficient to at least partially centrifuge particles present within the bleed air into the radially outer narrow tip of said cavity and convey the particles circumferentially thereabout to the particle outlet, wherein air flowing out from the clean air outlet is thereby substantially free of particles.