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A combination ceramic and metal turbine rotor for use in high temperature gas turbine engines includes a metal rotor disc having a rim with a plurality of circumferentially spaced blade root retention slots therein to receive a plurality of ceramic blades, each including side platform segments there

A combination ceramic and metal turbine rotor for use in high temperature gas turbine engines includes a metal rotor disc having a rim with a plurality of circumferentially spaced blade root retention slots therein to receive a plurality of ceramic blades, each including side platform segments thereon and a dovetail configured root slidably received in one of the slots. Adjacent ones of the platform segments including edge portions thereon closely spaced when the blades are assembled to form expansion gaps in an annular flow surface for gas passage through the blades and wherein the assembly further includes a plurality of unitary seal members on the rotor connected to its rim and each including a plurality of spaced, axially extending, flexible fingers that underlie and conform to the edge portions of the platform segments and which are operative at turbine operating temperatures and speeds to distribute loading on the platform segments as the fingers are seated against the underside of the blade platforms to seal the gaps without undesirably stressing thin web ceramic sections of the platform.

대표청구항 ▼

In a high temperature gas turbine engine ceramic and metal turbine rotor assembly of the type including a metal rotor disc having a rim with a plurality of circumferentially spaced retention slots therein and end faces thereon, and a plurality of ceramic blades, each blade including side platform se

In a high temperature gas turbine engine ceramic and metal turbine rotor assembly of the type including a metal rotor disc having a rim with a plurality of circumferentially spaced retention slots therein and end faces thereon, and a plurality of ceramic blades, each blade including side platform segments thereon, a blade stalk and a dependent dovetail configured root slidably received in one of said slots, adjacent ones of said platform segments including edge portions thereon closely spaced when said blades are assembled on said disc to form a substantially closed bottom surface for gas flow through said blades, an improved platform seal assembly comprising a plurality of seal members each having a flat ring segment and a plurality of integral fingers disposed generally at 90°to the plane of said ring segment, each of said seal members being fabricated from a high temperature resistant metal and being on the order of 0.005 inches in thickness so that each of said fingers is highly flexible yet light in weight, a plurality of blade connector plates corresponding in number to the number of said seal members and adapted for disposition on one of said rotor disc end faces, means rigidly attaching respective ones of said flat ring segments to corresponding ones of said blade connector plates, and means rigidly attaching each of said connector plates to said rotor disc with said ring segments captured between said rotor and said connector plate thereby to seal between said blade stalks to prevent gas bypass therebetween while accurately positioning each of said fingers beneath said closely spaced edge portions of said platform segments so that said fingers overlap a gap found between said platform segments, said fingers being responsive to rotation of said disc to be centrifugally displaced and flexed against the underside of said platform segments to distribute seal loads at the edge portions thereon to prevent stress concentrations at the platform while sealing said gap therebetween so as to prevent gas bypass through said flow path bottom during operation of the gas turbine engine.