| 摘要 |
An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members shaped to engage slotted hook members formed on the first stage disk to form a bayonet connection, and complementary lip members for engaging lobe members formed on the second stage disk by virtue of split rings, thereby eliminating the need for a bolted connection between the thermal shield and disks and facilitating attachment and removal of the thermal shield. The thermal shield includes an annular impeller which is positioned rearwardly of the first stage disk, the impeller including bayonet connection with the disk which restrains the impeller from axial deflection, but permits radial deflection in response to thermal changes. The thermal shield also includes an annular bore, attached to and extending radially inwardly from the thermal shield, and rotating in a plane substantially normal to a rotational axis of the shaft mounting the disks. The bore is shaped to have a center of mass out of the plane of rotation, so that rotation of the bore creates a moment which urges the bore to deflect toward the upstream disk, thereby compensating for a pressure differential across the face of the bore as cooling air is pumped by the impeller radially outwardly toward the end of the first stage disk.
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