US Patent 11428104 Partition arrangement for gas turbine engine and method

The turbine rotor assembly can include a turbine rotor disc drivingly mounted to a shaft for rotation about a rotation axis and having a central aperture extending coaxially with the shaft through the turbine rotor disc and being defined by a radially inner surface of the turbine rotor disc, a cavity downstream of and housing at least a part of the turbine rotor disc, a nut secured to the shaft and extending across the central aperture, a first air passage defined between an outer surface of the nut and the radially inner surface of the turbine rotor disc and fluidly connected to the cavity, a second air passage defined radially inward of the first air passage by an inner surface of the shaft and an inner surface of the nut.