Abstract: A method and apparatus for forming a hardened contact surface on a shroud of a turbomachinery blade comprising casting the blade and internal shroud with a metal insert into the casting mold so that the blade is cast with the insert in place. The insert may be formed with a projection extending from a wear surface of the shroud into the plane of the blade shroud such that the material from which the blade is made is cast about the projection to firmly and mechanically hold the insert in place. Each insert is preferably formed of a relatively low coefficient of friction and high wear resistant material whereby contact between abutting inserts on adjacent shroud surfaces have a high degree of slippage.

Abstract: Disclosed is a vibration damped gas turbine engine airfoil row. The airfoil row, comprising first and second coaxial, circular spools and airfoils extending radially therebetween, is cast in at least one piece and then the second or inner spool is cut between adjacent airfoils. Damping inserts are held in place adjacent the inner surface of the second spool by a retaining means.

Abstract: The present invention discloses a turbomachinery blading configuration. The configuration includes a circumferential recess in a blade support structure and a plurality of blades. Each blade has a platform for mounting the blade within the recess. Each platform includes oppositely directed, generally circumferentially facing edges, each edge having a first and second axial surfaces separated by a recess. The surfaces contact matching surfaces on adjacent blades thereby determining predictable load paths for tangential and twisting moment reaction forces acting on the blades.