Abstract: The invention comprises the use of a thermal barrier coating on a member of a gas turbine engine component with one surface of the member exposed to high temperature but not exposed to high velocity gases, as an insulating material to slow the heat transfer to the substrate of the component member and allow thermal gradients within acceptable material limits between the thermal barrier coated member and the remainder of the component. In a particular application, the use of a thermal barrier coating enables making a high pressure turbine nozzle integral with a discourager seal lip, eliminating fasteners protruding into the rotor/stator cavity and split lines between segments of the prior art that allowed high temperature gas ingestion further into the cavity and caused windage losses.

Abstract: A single turbomachine support structure provides both close tolerance radial positioning of a turbine shroud and close tolerance axial positioning of a vane. Radial movement of the vane without attendant radial movement of the shroud is accommodated by the use of surfaces designed to minimize constraint between the vane and the support structure. The linkage is further provided with cooling means to isolate thermal variations proximate the vane end thereof from the support structure end thereof.

Abstract: Hot gas recirculation is eliminated between the trailing edge of a turbine shroud and the leading edge of a downstream vane by a tongue-and-groove interconnection between the two parts and a passage of cooling air through the interconnection to exhaust against the vane outer band and flow into the main gas stream. The shroud with its supporting structure is thereby maintained at substantially uniform temperatures around its circumference so as to present a round, close-tolerance relationship to its circumscribed turbine blade row.