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A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned dow

A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

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1. A turbine engine incorporating a fine particle separation means, the turbine engine comprising: a radial compressor that rotates about a longitudinal axis, and which compresses air fed thereto;a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal a

1. A turbine engine incorporating a fine particle separation means, the turbine engine comprising: a radial compressor that rotates about a longitudinal axis, and which compresses air fed thereto;a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and which decreases a velocity of and increases a static pressure of the compressed air exiting the radial compressor;a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction; andan extraction slot at the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward, with respect to the longitudinal axis, from the outer annular wall at a position downstream axially along the flow path from the arc, the extraction slot also being positioned downstream axially along the flow path from the arc, wherein the extraction slot is defined between the outer annular wall and an inner radial wall of the scavenge plenum that is offset radially inward from the outer annular wall such that the extraction slot occupies about 1% to about 15% of an area of the flow path, measured with respect to a plane perpendicular to the longitudinal axis. 2. The turbine engine of claim 1, wherein the flow path comprises a portion of a deswirl assembly. 3. The turbine engine of claim 2, wherein the deswirl assembly comprises a plurality of vanes that reduce a tangential component of the compressed air, the plurality of vanes being located downstream from the arc. 4. The turbine engine of claim 3, wherein the scavenge plenum is positioned adjacent to and radially outward from, with respect to the longitudinal axis, the plurality of vanes. 5. The turbine engine of claim 1, wherein the scavenge plenum comprises a particle withdrawal port. 6. The turbine engine of claim 1, further comprising a combustion section immediately downstream of the flow path. 7. The turbine engine of claim 1, wherein the turbine engine is a propulsion-type turbine engine or an auxiliary power unit (APU). 8. The turbine engine of claim 1, wherein the extraction slot comprises either an axi-symmetric annulus or a plurality of annularly-disposed holes. 9. The turbine engine of claim 1, further comprising a plurality of holes along the outer annular wall that fluidly connect with a second scavenge plenum, the plurality of holes being positioned along the arc, the second scavenge plenum being positioned adjacent to and radially outward from, with respect to the longitudinal axis, the arc. 10. A turbine engine incorporating a fine particle separation means, the turbine engine comprising: a radial compressor that rotates about a longitudinal axis, and which compresses air fed thereto;a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and which decreases a velocity of and increases a static pressure of the compressed air exiting the radial compressor;a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction; anda plurality of holes formed into the outer annular wall that fluidly connect with a scavenge plenum, the plurality of holes being positioned along the arc such that the compressed air flowing past the holes has a radially-outward flow component, the scavenge plenum being positioned adjacent to and radially outward from, with respect to the longitudinal axis, the arc. 11. The turbine engine of claim 10, wherein the flow path comprises a portion of a deswirl assembly. 12. The turbine engine of claim 11, wherein the deswirl assembly comprises a plurality of vanes that reduce a tangential component of the compressed air, the plurality of vanes being located downstream from the arc. 13. The turbine engine of claim 10, wherein the holes are angled circumferentially from about 25 to about 65 degrees with respect to the outer annular wall. 14. The turbine engine of claim 10, wherein the holes are angled axially rearward from about 5 to about 20 degrees with respect to the outer annular wall. 15. The turbine engine of claim 10, wherein the scavenge plenum comprises a particle withdrawal port. 16. The turbine engine of claim 10, further comprising a combustion section immediately downstream of the flow path. 17. A turbine engine incorporating a fine particle separation means, the turbine engine comprising: a compressor that rotates about a longitudinal axis, and which compresses air fed thereto;a flow path positioned downstream from the compressor, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction; andboth of 1) an extraction slot in the outer annular wall that fluidly connects with a first scavenge plenum, the first scavenge plenum being positioned adjacent to and radially outward, with respect to the longitudinal axis, from the outer annular wall at a position downstream axially along the flow path from the arc, the extraction slot also being positioned downstream axially along the flow path from the arc, and 2) a plurality of holes along the outer annular wall that fluidly connect with a second scavenge plenum, the plurality of holes being positioned along the arc, the second scavenge plenum being positioned adjacent to and radially outward from, with respect to the longitudinal axis, the arc. 18. The turbine engine of claim 17, wherein the compressor comprises a radial or mixed-flow compressor.