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A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The

A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

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1. A compressor comprising: a housing;a rotor mounted within the housing and having a first leading edge and a first trailing edge, the rotor operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction;an impeller mounted within the housing having a

1. A compressor comprising: a housing;a rotor mounted within the housing and having a first leading edge and a first trailing edge, the rotor operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction;an impeller mounted within the housing having a second leading edge and a second trailing edge, the impeller operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction; anda shroud at least partially surrounding the impeller, the shroud having an opening therein to at least facilitate allowing the air to travel upstream of the opening away from the impeller and to return to the impeller at a location that is upstream of the opening. 2. The compressor of claim 1, wherein the opening allows the air to circulate from the impeller from a second location that is downstream of the second leading edge to the second leading edge via the opening. 3. The compressor of claim 2, wherein the housing forms a plenum fluidly coupling the opening to the second leading edge. 4. The compressor of claim 3, wherein the housing forms a transition duct fluidly coupling the plenum to the second leading edge. 5. The compressor of claim 4, wherein the transition duct is formed between the rotor and the impeller. 6. The compressor of claim 5, further comprising: a stator mounted within the housing between the rotor and the transition duct. 7. The compressor of claim 1, further comprising: a radial diffuser coupled to the impeller, the radial diffuser configured to diffuse the air and to direct the air from an approximately radial flow to an approximately axial flow. 8. A compressor comprising: a housing;a rotor mounted within the housing and having a first leading edge and a first trailing edge, the rotor operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction;an impeller mounted within the housing having a second leading edge and a second trailing edge, the second leading edge being downstream from the rotor and upstream form the second trailing edge, the impeller operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction; anda first shroud at least partially surrounding the impeller, the first shroud having a first opening therein to at least facilitate allowing the air to circulate upstream from the impeller to the first leading edge. 9. The compressor of claim 8, wherein the housing forms a first plenum fluidly coupling the first opening to the first leading edge. 10. The compressor of claim 9, further comprising: a second shroud at least partially surrounding the rotor, the second shroud having a second opening therein fluidly coupling the first plenum to the first leading edge. 11. The compressor of claim 10, further comprising: a flange mounted within the housing between the first plenum and the second opening, the flange having a third opening therein to at least facilitate allowing movement of the air from the first plenum toward the second opening. 12. The compressor of claim 11, wherein the housing further forms a second plenum between the flange and the second shroud, the second plenum fluidly coupling the third opening to the second opening. 13. The compressor of claim 8, wherein the rotor is disposed upstream of the impeller. 14. The compressor of claim 8, wherein the housing forms a transition duct fluidly coupling the rotor to the impeller. 15. The compressor of claim 14, further comprising: a stator mounted within the housing between the rotor and the transition duct. 16. The compressor of claim 15, further comprising: a radial diffuser coupled to the impeller, the radial diffuser configured to diffuse the air and to direct the air from an approximately radial flow to an approximately axial flow. 17. A gas turbine engine, comprising: a housing;a turbine formed within the housing and configured to receive a combustion gas and operable, upon receipt thereof, to supply a drive force;a combustor formed within the housing and configured to receive compressed air and fuel and operable, upon receipt thereof, to supply the combustion gas to the turbine; anda compressor formed within the housing and configured to supply the compressed air to the combustor, the compressor comprising: a rotor mounted within the housing and having a first leading edge and a first trailing edge, the rotor operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction;an impeller mounted within the housing having a second leading edge and a second trailing edge, the second leading edge being downstream from the rotor and upstream form the second trailing edge, the impeller operable, upon rotation thereof, to receive the air discharged from the rotor and, to further compress the air, and to discharge the air in an approximately radial direction; anda shroud at least partially surrounding the rotor, the shroud having an opening therein to at least facilitate allowing the air to circulate from the impeller upstream to the first leading edge or the second leading edge. 18. The gas turbine engine of claim 17, wherein the housing forms a plenum fluidly coupling the opening to the second leading edge. 19. The gas turbine engine of claim 17, wherein the housing forms a plenum fluidly coupling the opening to the first leading edge. 20. The gas turbine engine of claim 19, further comprising: a second shroud at least partially surrounding the rotor, the second shroud having a second opening therein to at least facilitate allowing movement of the air from the plenum toward the first leading edge.