Turbine assemblies with impingement cooling

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, and
• an 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.

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 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.