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A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a tur

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

대표청구항 ▼

1. A gas turbine engine assembly, comprising: a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow;a stator assembly comprising a stator vane extending into the mainstream gas flow; anda turbine rotor as

1. A gas turbine engine assembly, comprising: a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow;a stator assembly comprising a stator vane extending into the mainstream gas flow; anda turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly, the turbine rotor assembly comprising a rotor disk having a forward side and an aft side,a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager,a rotor blade mounted on the rotor platform extending into the mainstream gas flow, andan aft seal plate mounted on the aft side of the rotor disk, the aft seal plate having a radius such that the aft seal plate protects the rotor platform from hot gas ingestion of the mainstream hot gas flow path into the turbine cavity, wherein the aft seal plate defines at least one cooling channel within an interior portion of the aft seal plate. 2. The gas turbine engine assembly of claim 1, wherein the aft seal plate has an outer periphery that is positioned adjacent the aft flow discourager. 3. The gas turbine engine assembly of claim 1, wherein the aft flow discourager overlaps the aft seal plate. 4. The gas turbine engine assembly of claim 1, wherein the at least one cooling channel is configured to provide cooling flow to the aft flow discourager. 5. The gas turbine engine assembly of claim 1, wherein the at least one cooling channel is configured to provide impingement cooling flow to the aft flow discourager. 6. The gas turbine engine assembly of claim 1, wherein the at least one cooling channel extends in a radial direction. 7. The gas turbine engine assembly of claim 6, wherein the rotor disk defines a disk channel configured to supply cooling flow to the at least one cooling channel. 8. The gas turbine engine assembly of claim 1, wherein the at least one cooling channel is oriented such that cooling flow strikes the aft flow discourager at about 90°. 9. The gas turbine engine assembly of claim 1, wherein the aft seal plate further includes at least one axial flange extending in an aft direction. 10. The gas turbine engine assembly of claim 6, wherein the at least one axial flange is positioned on a peripheral portion of aft seal plate. 11. A turbine assembly of a gas turbine engine assembly defining a mainstream hot gas flow path that receives mainstream hot gas flow, the assembly comprising: a rotor disk having a forward side, an aft side, and a circumferential periphery,a rotor platform positioned on the periphery of the rotor disk, the rotor platform defining an aft flow discourager,a rotor blade mounted on the rotor platform extending into the mainstream gas flow, andan aft seal plate mounted on the aft side of the rotor disk, the aft seal plate defining at least one cooling channel configured to deliver cooling flow to the aft flow discourager. 12. The turbine assembly of claim 11, wherein the at least one cooling channel is configured to provide impingement cooling flow to the aft flow discourager. 13. The turbine assembly of claim 11, wherein the at least one cooling channel extends in a radial direction. 14. The turbine assembly of claim 11, wherein the rotor disk defines a disk channel configured to supply cooling flow to the at least one cooling channel. 15. The turbine assembly of claim 11, wherein the at least one cooling channel is oriented such that cooling flow strikes the aft flow discourager at about 90°. 16. The turbine assembly of claim 11, wherein the aft seal plate further includes at least one axial flange extending in an aft direction. 17. The turbine assembly of claim 16, wherein the at least one axial flange is positioned on a peripheral portion of aft seal plate. 18. The turbine assembly of claim 16, wherein the aft seal plate has a radius such that the aft seal plate discourages hot gas ingestion from the mainstream hot gas flow path. 19. A gas turbine engine assembly, comprising: a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow;a stator assembly comprising a stator vane extending into the mainstream gas flow; anda turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly, the turbine rotor assembly comprising a rotor disk having a forward side and an aft side,a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager,a rotor blade mounted on the rotor platform extending into the mainstream gas flow, andan aft seal plate mounted on the aft side of the rotor disk, the aft seal plate having a radius such that the aft seal plate discourages hot gas ingestion from the mainstream hot gas flow path, the aft seal plate defining at least one radially extending cooling channel configured to provide impingement cooling flow to the aft flow discourager, the aft seal plate further including at least one axial flange extending in an aft direction and positioned on a peripheral portion of aft seal plate. 20. The gas turbine engine assembly of claim 1, wherein the rotor disk includes disk passage to direct cooling air between the forward side and the aft side, and wherein the aft seal plate includes a seal between the aft seal plate and the rotor disk, the seal positioned such that the cooling air from the disk passage is directed into the at least one cooling channel.