Integral turbine nozzle support and discourager seal

摘要

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.