General Electric Company

L Timothy Rasch

Stephen Joseph Ferrigno

John Peter Heyward

Ronald Lance Galley

Jeffrey J Reverman

Timothy Lee Siebert

Jeffery John Reverman

A method is provided for removing a dense ceramic thermal barrier coating (TBC) from an article surface over which the TBC is disposed, the article surface including an edge at which at least a portion of an interface between the article surface and the TBC is exposed. The interface includes at least one material selected from Al, Ti, Cr, Zr and their oxides. The method comprises subjecting at least the exposed interface to a reducing gas at a temperature of at least 1600&deg; F. to separate the TBC from the article surface. The reducing gas is subjected for a time sufficient for the gas to penetrate the interface at least by converting to a gaseous compound at least one material of the group at the interface, and for the TBC to be removed by separation from the article surface.

Method for removing a dense ceramic thermal barrier coating from a surface

A turbine engine vane segment, including spaced apart band or platform members and at least one airfoil member carried at metallic bonds between the platform members, is improved by providing at least one, but not necessarily all, of the segment members as an improved member having a directionally oriented Ni base superalloy microstructure with a stress rupture strength greater than the stress rupture strength of the balance of the segment members, which have a conventional generally equiaxed microstructure. For example, the balance of the members are conventionally cast from a Co base alloy. The coefficient of thermal expansion of the improved member is different from that of the balance of the members. A metallic bond including a brazed structure is provided between the improved member and the balance of the members, possessing strength sufficient to carry the stresses caused by differences in coefficients of thermal expansion of the dissimilar materials.

Turbine engine vane segment

An airfoil and a band or platform member of a vane segment, such as of a turbine engine, are bonded at a non-linear clearance slot formed between a shelf in the band and an end and edge of the airfoil. A reservoir bead of a bonding alloy slurry is deposited at one slot opening, a metallic powder is packed into the slot, and another reservoir bead is applied at a slot second opening substantially to close the slot and entrap the powder therein. Then the reservoir beads and powder are heated to flow material of the beads into the clearance slot. This bonds the airfoil and band securely at a deep pocket or blind slot.

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Fairfield, OH, United States of America

L Timothy Rasch