Patent ID: 8616832

Claim:
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; and a 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, and an 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.