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AssigneeGeneral Motors Corporation
InventorsLawrence E. Brown, David L. Clingman, Michael J. Barber, Kenneth R. Cross
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An abrasive system and a processing procedure is provided which permits the direct installation of a thick abrasive blade tip cap onto a cast single crystal turbine rotor blade during a single heating schedule requiring only one furnace operation. The composition of the abrasive blade tip cap advantageously utilizes the high temperature performance capabilities of the single crystal alloy without significantly affecting its mechanical properties as a consequence of the processing necessary to permanently bond the abrasive blade tip cap to the rotor blade. A semi-rigid blade tip cap preform is first formed and positioned on the tip of the rotor blade. The preform and rotor blade are then heated in a vacuum furnace according to a temperature schedule entailing heating rates, holding temperatures and durations which are sufficient to bond and consolidate the preform. The rotor blade is then rapidly cooled in the vacuum furnace to retain the single crystal structure of the rotor blade.
An abrasive blade tip cap preform for bonding to a rotor blade tip to form an abrasive rotor blade tip cap, said abrasive blade tip cap preform comprising:
An abrasive blade tip cap preform for bonding to a rotor blade tip to form an abrasive rotor blade tip cap, said abrasive blade tip cap preform comprising:
A rotor blade comprising:
Dependencies are inferred from the claim text.